EP2027368A1 - Turbine à gaz et procédé de fonctionnement d'une turbine à gaz - Google Patents

Turbine à gaz et procédé de fonctionnement d'une turbine à gaz

Info

Publication number
EP2027368A1
EP2027368A1 EP06753264A EP06753264A EP2027368A1 EP 2027368 A1 EP2027368 A1 EP 2027368A1 EP 06753264 A EP06753264 A EP 06753264A EP 06753264 A EP06753264 A EP 06753264A EP 2027368 A1 EP2027368 A1 EP 2027368A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine
rotor
stopping
generator
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
EP06753264A
Other languages
German (de)
English (en)
Other versions
EP2027368B1 (fr
EP2027368B9 (fr
Inventor
Peter Geiger
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2027368A1 publication Critical patent/EP2027368A1/fr
Publication of EP2027368B1 publication Critical patent/EP2027368B1/fr
Application granted granted Critical
Publication of EP2027368B9 publication Critical patent/EP2027368B9/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/34—Turning or inching gear
    • F01D25/36—Turning or inching gear using electric motors
    • 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
    • F01D21/06—Shutting-down
    • 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
    • F01D21/08—Restoring position

Definitions

  • the invention relates to a gas turbine, in particular an aircraft engine, according to the preamble of claim 1. Furthermore, the invention relates to a method for operating a gas turbine, in particular an aircraft engine, according to the preamble of claim. 7
  • Gas turbines such as aircraft engines, have several assemblies, such as at least one compressor, a combustion chamber and at least one turbine.
  • the rotor-side components of the or each turbine are exposed to high temperatures.
  • the rotor-side components of the or each turbine cool down at standstill.
  • different temperatures develop on a bottom side and a top side due to convection. Due to these different temperatures at the top and the bottom of the rotor, a curvature thereof, a so-called rotor bow, can form.
  • the curvature of the rotor can be so strong that rotor-side rotor blades come to rest on a housing of the turbine and stator-side vanes on a hub of the rotor. In this case, a restart of the gas turbine is only possible if after a longer cooling time, the rotor bow has receded again. Otherwise it would be damaged if the gas turbine restarts.
  • the present invention is based on the problem to provide a novel gas turbine and a novel method for operating a gas turbine.
  • the or each generator after stopping the gas turbine, can be used as a motor to drive a rotor of the respective turbine after switching off the gas turbine for a certain period of time and thereby cause a uniform cooling of the rotor.
  • the rotor of the respective turbine for a certain period of time after switching off the gas turbine.
  • This allows a uniform cooling of the Rotor of the respective turbine causes or be established. Due to the fact that the rotor of the respective turbine is rotationally driven after stopping the gas turbine for a certain period of time, caused by convection, different temperatures at the bottom and the top of the rotor are avoided, so that the formation of a rotor curvature or a rotor bows is prevented.
  • the invention allows earlier restarting of a gas turbine after it has been shut down.
  • the or each generator drives the rotor of the respective turbine at a speed of the order of magnitude of between 0.1 rpm and 10 rpm, in particular of the order of magnitude between 0.2 rpm and 5 rpm. min, on.
  • an oil circulation is additionally effected or established after stopping, so as to prevent a ⁇ lverkokung after switching off the gas turbine.
  • Gas turbines have several assemblies, namely at least one compressor, a combustion chamber and at least one turbine.
  • gas turbines are known from the prior art, which have two compressors and two turbines. These are then a low-pressure compressor, a high-pressure compressor, a high-pressure turbine and a low-pressure turbine.
  • gas turbines with three compressors and three turbines are known, which are then a low pressure compressor, a medium pressure compressor, a high pressure compressor, a high pressure turbine, a medium pressure turbine and a low pressure turbine.
  • One compressor each is connected to a turbine via a shaft.
  • the high-pressure turbine is connected to the high-pressure compressor and the low-pressure turbine to the low-pressure compressor via one shaft.
  • the medium-pressure turbine is further coupled to the medium-pressure compressor via a shaft.
  • Gas turbines with generators are already known from the prior art, with the generators serving to generate electrical energy.
  • the low-pressure turbine may be associated with a generator which draws power during operation of the gas turbine of the low-pressure turbine and generates electrical energy therefrom. The electrical energy generated by the generator is then used for operating cultivation aggregates of the gas turbine or for operating other electrical devices.
  • the or each generator which serves to generate electrical energy during operation of the gas turbine is used as an engine after switching off the gas turbine and is therefore operated in engine operation.
  • the or each generator then converts, during engine operation, electrical energy into mechanical energy for driving the respective turbine rotor, wherein the respective turbine rotor is driven at a relatively low speed.
  • the respective turbine rotor with a speed in the order of 0.1 U / min to 10 U / min, preferably in the order of 0.2 U / min to 5 U / min, is driven.
  • the generator of the low-pressure turbine is operated in engine operation in accordance with the present invention after switching off the gas turbine to the rotor of the low-pressure turbine or the rotor-side components of the low-pressure turbine for a to drive or rotate certain time duration.
  • a uniform cooling of the rotor-side assemblies of the low-pressure turbine can be effected. Different temperatures on an upper side and a lower side of the rotor-side assemblies of the low-pressure turbine can be avoided.
  • an oil circulation in the lubrication system of the respective turbine is established, so as an oil coking after to prevent the shutdown of the gas turbine.
  • the oil circulation may be effected by the or each generator also driving an oil pump after shutting off the gas turbine to effect the oil circulation.
  • the turbine rotor driven by the generator can effect an oil circulation in which, for example, ribs assigned to the rotor cause a pumping effect in the region of a bearing sump of a rotor bearing and thus cause an oil circulation. In any case, however, prevents an overheating of the oil by an after the shutdown of the gas turbine caused oil circulation and thus reduces ⁇ lverko- kungsgefahr.
  • the or each generator may also be operated in engine mode so as to rotate for servicing the rotor-side assemblies of the respective turbine.
  • the inspection of rotor-side blades, for example in the so-called Boroskopieren be facilitated.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Control Of Eletrric Generators (AREA)
  • Motor Or Generator Cooling System (AREA)

Abstract

L'invention concerne une turbine à gaz, en particulier un moteur d'avion, comprenant au moins un compresseur, une chambre de combustion et au moins une turbine. Selon l'invention, au moins un générateur est affecté à au moins une turbine pour produire de l'énergie et, après l'arrêt de la turbine à gaz, le ou chaque générateur est utilisable comme moteur pour entraîner pendant un certain temps un rotor de la turbine respective après l'arrêt de la turbine à gaz et provoquer ainsi un refroidissement uniforme du rotor.
EP06753264A 2006-06-10 2006-06-10 Fonctionnement d'une turbine à gaz d'avion Expired - Fee Related EP2027368B9 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/DE2006/000996 WO2007140730A1 (fr) 2006-06-10 2006-06-10 Turbine à gaz et procédé de fonctionnement d'une turbine à gaz

Publications (3)

Publication Number Publication Date
EP2027368A1 true EP2027368A1 (fr) 2009-02-25
EP2027368B1 EP2027368B1 (fr) 2010-01-06
EP2027368B9 EP2027368B9 (fr) 2012-01-18

Family

ID=37866346

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06753264A Expired - Fee Related EP2027368B9 (fr) 2006-06-10 2006-06-10 Fonctionnement d'une turbine à gaz d'avion

Country Status (4)

Country Link
US (1) US9121309B2 (fr)
EP (1) EP2027368B9 (fr)
DE (1) DE112006003994A5 (fr)
WO (1) WO2007140730A1 (fr)

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US10823079B2 (en) 2016-11-29 2020-11-03 Raytheon Technologies Corporation Metered orifice for motoring of a gas turbine engine
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Also Published As

Publication number Publication date
US20090301053A1 (en) 2009-12-10
EP2027368B1 (fr) 2010-01-06
WO2007140730A1 (fr) 2007-12-13
US9121309B2 (en) 2015-09-01
EP2027368B9 (fr) 2012-01-18
DE112006003994A5 (de) 2009-05-20

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