EP2027368B9 - Method of operating a gas turbine engine - Google Patents

Method of operating a gas turbine engine Download PDF

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Publication number
EP2027368B9
EP2027368B9 EP06753264A EP06753264A EP2027368B9 EP 2027368 B9 EP2027368 B9 EP 2027368B9 EP 06753264 A EP06753264 A EP 06753264A EP 06753264 A EP06753264 A EP 06753264A EP 2027368 B9 EP2027368 B9 EP 2027368B9
Authority
EP
European Patent Office
Prior art keywords
turbine
rotor
gas turbine
generator
aircraft engine
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
EP06753264A
Other languages
German (de)
French (fr)
Other versions
EP2027368B1 (en
EP2027368A1 (en
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 GmbH
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
Priority to PCT/DE2006/000996 priority Critical patent/WO2007140730A1/en
Publication of EP2027368A1 publication Critical patent/EP2027368A1/en
Publication of EP2027368B1 publication Critical patent/EP2027368B1/en
Application granted granted Critical
Publication of EP2027368B9 publication Critical patent/EP2027368B9/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/34Turning or inching gear
    • F01D25/36Turning or inching gear using electric motors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04Shutting-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
    • F01D21/06Shutting-down
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04Shutting-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
    • F01D21/08Restoring position

Abstract

The invention relates to a gas turbine, in particular to an aircraft engine, having at least one compressor, a combustion chamber and at least one turbine, wherein at least one generator for generating electrical energy is assigned to at least one turbine. According to the invention, after the shutdown of the gas turbine, the or each generator can be used as a motor in order to drive a rotor of the respective turbine for a certain period after the shutdown of the gas turbine and in this way effect uniform cooling of the rotor.

Description

  • The invention relates to a method for operating an aircraft engine, according to the preamble of claim 1.
  • Gas turbines in the form of aircraft engines have several components, such as at least one compressor, a combustion chamber and at least one turbine. During operation of the gas turbine, in particular the rotor-side components of the or each turbine are exposed to high temperatures. In the context of the prior art, during or after switching off the gas turbine, the rotor-side components of the or each turbine cool down at standstill. When cooling the rotor-side components of a turbine at a standstill convection formed on a bottom and a top of different temperatures. 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 blades come to rest on a housing of the turbine and stator 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.
  • From the document US 6 031 294 A For example, a turbogenerator is known in which a gas turbine drives an electric generator. The generator is also operable as a motor so that it is usable for starting the gas turbine. The gas turbine has a heat exchanger / storage in the form of a so-called. Recuperator, which is heated by the turbine exhaust gas and gives off heat to the compressor supply to increase the efficiency of the gas turbine process. After switching off the gas turbine, a build-up of heat may occur in the recuperator region, which may be harmful especially for the electrical components of the generator. To remedy this, it is proposed, after switching off the gas turbine, that the rotor still rotate for a certain time, with the generator running in engine mode in order to generate a cooling air flow.
  • On this basis, the present invention based on the problem to provide a novel method for operating an aircraft engine.
  • This problem is solved by a method according to claim 1.
  • For the purposes of the present invention, it is proposed to drive the rotor of the respective turbine for a certain period of time after stopping the aircraft engine. In this way, a uniform cooling of the rotor of the respective turbine can be effected or established. Due to the fact that the rotor of the respective turbine is driven in rotation 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 enables an earlier restart of an aircraft engine after it has been parked.
  • The or each generator drives after stopping the aircraft engine, the rotor of the respective turbine at a speed in the order of 0.1 U / min to 10 U / min.
  • According to an advantageous embodiment of the invention, an oil circulation is additionally effected or established after stopping, so as to prevent Ölverkokung after stopping the aircraft engine.
  • Preferred embodiments of the invention will become apparent, without being limited thereto, from the dependent claims and the description below.
  • Gas turbines in the form of aircraft engines have several components, namely at least one compressor, a combustion chamber and at least one turbine. Thus, 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. Furthermore, 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. In gas turbines with two compressors and two turbines, the high-pressure turbine is connected to the high-pressure compressor and the low-pressure turbine to the low-pressure compressor via one shaft. In a gas turbine with three compressors and three turbines, 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. Thus, for example, 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.
  • For the purposes of the present invention, it is proposed to rotate the rotor of the or each turbine for a certain period of time after the shutdown of the gas turbine, thereby enabling a uniform cooling of the rotor-side assemblies of the respective turbine rotor. In this case, in the sense of the invention, 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. It is within the meaning of the present invention that 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.
  • If, for example, the low-pressure turbine of a gas turbine is assigned a generator for generating electrical energy, 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. In this way, 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. It is also possible to drive the rotor of a medium-pressure turbine and a high-pressure turbine after stopping the gas turbine by a generator associated with the respective turbine for a predetermined period of time.
  • It is also within the meaning of the present invention that after stopping the gas turbine additionally 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. For example, 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. Alternatively, 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, is prevented by a shutdown of the gas turbine oil circulation overheating of the oil, thus reducing a Ölverkokungsgefahr.
  • During servicing of a gas turbine, 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. As a result, the inspection of rotor-side blades, for example in the so-called Boroskopieren be facilitated.

Claims (3)

  1. A method for operating an aircraft engine having at least one compressor, a combustion chamber and at least one turbine,
    characterised in that
    after the shut-down of the aircraft engine a rotor of the or each turbine is driven for a certain period of time in order to effect hereby uniform cooling of the rotor, wherein the rotor of the respective turbine is driven at a speed of the order of magnitude of between 0.1 rpm and 10 rpm.
  2. A method according to claim 1,
    characterised in that
    after the shut-down of the aircraft engine the rotor of the respective turbine is driven at a speed of the order of magnitude of between 0.2 rpm and 5 rpm.
  3. A method according to claim 1 or 2,
    characterised in that
    after the shut-down oil-circulation is effected or established in order to prevent oil-coking after the shut-down of the aircraft engine.
EP06753264A 2006-06-10 2006-06-10 Method of operating a gas turbine engine Active EP2027368B9 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/DE2006/000996 WO2007140730A1 (en) 2006-06-10 2006-06-10 Gas turbine and method of operating a gas turbine

Publications (3)

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

Family

ID=37866346

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06753264A Active EP2027368B9 (en) 2006-06-10 2006-06-10 Method of operating a gas turbine engine

Country Status (4)

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

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ITFI20110247A1 (en) * 2011-11-14 2013-05-15 Nuovo Pignone Spa "Device and method for slow turning of an aeroderivative gas turbines"
US9605597B2 (en) * 2013-06-13 2017-03-28 Solar Turbines Incorporated Variable frequency drive power ride thru
US9771932B2 (en) * 2014-02-14 2017-09-26 The Boeing Company Apparatus, controller and method for controlling the cool down of an aircraft engine rotor
WO2015193979A1 (en) * 2014-06-18 2015-12-23 株式会社日立製作所 Multi-shaft variable-speed gas turbine device and control method therefor
FR3027061A1 (en) * 2014-10-10 2016-04-15 Turbomeca Method and device for notifying a complete stop authorization of an aircraft gas turbine engine
FR3038003A1 (en) * 2015-06-24 2016-12-30 Snecma Turbomachine accessory box provided with an electric motor-alternator and method of operating such a box
US10174678B2 (en) 2016-02-12 2019-01-08 United Technologies Corporation Bowed rotor start using direct temperature measurement
US10508601B2 (en) 2016-02-12 2019-12-17 United Technologies Corporation Auxiliary drive bowed rotor prevention system for a gas turbine engine
US10125636B2 (en) 2016-02-12 2018-11-13 United Technologies Corporation Bowed rotor prevention system using waste heat
US10508567B2 (en) 2016-02-12 2019-12-17 United Technologies Corporation Auxiliary drive bowed rotor prevention system for a gas turbine engine through an engine accessory
US10040577B2 (en) 2016-02-12 2018-08-07 United Technologies Corporation Modified start sequence of a gas turbine engine
US9664070B1 (en) * 2016-02-12 2017-05-30 United Technologies Corporation Bowed rotor prevention system
US10125691B2 (en) 2016-02-12 2018-11-13 United Technologies Corporation Bowed rotor start using a variable position starter valve
US10539079B2 (en) 2016-02-12 2020-01-21 United Technologies Corporation Bowed rotor start mitigation in a gas turbine engine using aircraft-derived parameters
US10443505B2 (en) 2016-02-12 2019-10-15 United Technologies Corporation Bowed rotor start mitigation in a gas turbine engine
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US10443507B2 (en) * 2016-02-12 2019-10-15 United Technologies Corporation Gas turbine engine bowed rotor avoidance system
EP3211184A1 (en) 2016-02-29 2017-08-30 United Technologies Corporation Bowed rotor prevention system and associated method of bowed rotor prevention
US10337405B2 (en) 2016-05-17 2019-07-02 General Electric Company Method and system for bowed rotor start mitigation using rotor cooling
US10358936B2 (en) 2016-07-05 2019-07-23 United Technologies Corporation Bowed rotor sensor system
US10533459B1 (en) * 2016-07-07 2020-01-14 Kenneth Knecht Slow turning gear adapter to eliminate turbine bucket wear
US10618666B2 (en) 2016-07-21 2020-04-14 United Technologies Corporation Pre-start motoring synchronization for multiple engines
EP3273006B1 (en) 2016-07-21 2019-07-03 United Technologies Corporation Alternating starter use during multi-engine motoring
US10221774B2 (en) 2016-07-21 2019-03-05 United Technologies Corporation Speed control during motoring of a gas turbine engine
US10384791B2 (en) 2016-07-21 2019-08-20 United Technologies Corporation Cross engine coordination during gas turbine engine motoring
US10583933B2 (en) 2016-10-03 2020-03-10 General Electric Company Method and apparatus for undercowl flow diversion cooling
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Also Published As

Publication number Publication date
US20090301053A1 (en) 2009-12-10
US9121309B2 (en) 2015-09-01
EP2027368B1 (en) 2010-01-06
EP2027368A1 (en) 2009-02-25
DE112006003994A5 (en) 2009-05-20
WO2007140730A1 (en) 2007-12-13

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