EP2027368B1 - Method of operating a gas turbine engine - Google Patents
Method of operating a gas turbine engine Download PDFInfo
- Publication number
- EP2027368B1 EP2027368B1 EP06753264A EP06753264A EP2027368B1 EP 2027368 B1 EP2027368 B1 EP 2027368B1 EP 06753264 A EP06753264 A EP 06753264A EP 06753264 A EP06753264 A EP 06753264A EP 2027368 B1 EP2027368 B1 EP 2027368B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine
- rotor
- gas turbine
- generator
- gas
- 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.)
- Expired - Fee Related
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
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- 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
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- 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 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.
- 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.
- 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.
- a turbogenerator 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 air in order to increase the efficiency of the gas turbine process.
- a build-up of heat may occur in the recuperator region, which may be harmful especially for the electrical components of the generator.
- the present invention based on the problem to provide a novel method for operating an aircraft engine.
- the rotor of the respective turbine for a certain period of time after stopping the aircraft engine.
- 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.
- an oil circulation is additionally effected or established after stopping, so as to prevent ⁇ lverkokung after stopping the aircraft engine.
- Gas turbines in the form of aircraft engines have several components, 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 during 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.
- 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, is prevented by a shutdown of the gas turbine oil circulation overheating of the oil, thus reducing a ⁇ lverkokungsgefahr.
- 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.
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- 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)
Description
Die Erfindung betrifft ein Verfahren zum Betreiben eines Flugtriebwerks, nach dem Oberbegriff des Anspruchs 1.The invention relates to a method for operating an aircraft engine, according to the preamble of claim 1.
Gasturbinen in Form von Flugtriebwerken verfügen über mehrere Baugruppen, so zum Beispiel über mindestens einen Verdichter, eine Brennkammer sowie mindestens eine Turbine. Im Betrieb der Gasturbine sind insbesondere die rotorseitigen Bauteile der oder jeder Turbine hohen Temperaturen ausgesetzt. Im Sinne des Standes der Technik kühlen beim bzw. nach dem Abstellen der Gasturbine die rotorseitigen Bauteile der oder jeder Turbine im Stillstand ab. Beim Abkühlen der rotorseitigen Bauteile einer Turbine im Stillstand bilden sich konvektionsbedingt an einer Unterseite und einer Oberseite unterschiedlicher Temperaturen aus. Bedingt durch diese unterschiedlichen Temperaturen an der Oberseite und der Unterseite des Rotors kann sich eine Krümmung desselben, ein sogenannter rotor bow, ausbilden. Die Krümmung des Rotors kann dabei so stark sein, dass rotorseitige Laufschaufeln an einem Gehäuse der Turbine sowie statorseitige Leitschaufeln an einer Nabe des Rotors zur Anlage kommen. In diesem Fall ist ein Wiederstarten der Gasturbine erst dann möglich, wenn sich nach einer längeren Abkühlzeit der rotor bow wieder zurückgebildet hat. Ansonsten würde bei einem Wiederstarten der Gasturbine dieselbe beschädigt werden.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.
Aus dem Dokument
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zum Betreiben eines Flugtriebwerks zu schaffen.On this basis, the present invention based on the problem to provide a novel method for operating an aircraft engine.
Dieses Problem wird durch ein Verfahren gemäß Anspruch 1 gelöst.This problem is solved by a method according to claim 1.
Im Sinne der hier vorliegenden Erfindung wird vorgeschlagen, nach dem Abstellen des Flugtriebwerks den Rotor der jeweiligen Turbine für eine bestimmte Zeitdauer anzutreiben. Hierdurch kann eine gleichmäßige Abkühlung des Rotors der jeweiligen Turbine bewirkt bzw. etabliert werden. Bedingt dadurch, dass der Rotor der jeweiligen Turbine nach dem Abstellen der Gasturbine für eine bestimmte Zeitdauer drehend angetrieben wird, werden durch Konvektionen bedingt, unterschiedliche Temperaturen an der Unterseite sowie der Oberseite des Rotors vermieden, so dass die Ausbildung einer Rotorkrümmung bzw. eines rotor bows verhindert wird. Durch die Erfindung wird ein früheres Wiederstarten eines Flugtriebwerks nach einem Abstellen desselben ermöglicht.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.
Dabei treibt der oder jeder Generator nach dem Abstellen des Flugtriebwerks den Rotor der jeweiligen Turbine mit einer Drehzahl in der Größenordnung zwischen 0,1 U/min bis 10 U/min an.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.
Nach einer vorteilhaften Weiterbildung der Erfindung wird nach dem Abstellen zusätzlich eine Ölzirkulation bewirkt bzw. etabliert, um so eine Ölverkokung nach dem Abstellen des Flugtriebwerks zu verhindern.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.
Bevorzugte Weiterbildungen der Erfindung ergeben sich, ohne hierauf beschränkt zu sein, aus den unteransprüchen und der nachfolgenden Beschreibung.Preferred embodiments of the invention will become apparent, without being limited thereto, from the dependent claims and the description below.
Gasturbinen in Form von Flugtriebwerken verfügen über mehrere Baugruppen, nämlich über mindestens einen Verdichter, eine Brennkammer sowie mindestens eine Turbine. So sind aus dem Stand der Technik Gasturbinen bekannt, die über zwei Verdichter und zwei Turbinen verfügen. Hierbei handelt es sich dann um einen Niederdruckverdichter, einen Hochdruckverdichter, eine Hochdruckturbine sowie eine Niederdruckturbine. Des weiteren sind Gasturbinen mit drei Verdichtern sowie drei Turbinen bekannt, wobei es sich hierbei dann um einen Niederdruckverdichter, einen Mitteldruckverdichter, einen Hochdruckverdichter, eine Hochdruckturbine, eine Mitteldruckturbine sowie eine Niederdruckturbine handelt.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.
Jeweils ein Verdichter ist mit einer Turbine über eine Welle verbunden. Bei Gasturbinen mit zwei Verdichtern und zwei Turbinen ist die Hochdruckturbine mit dem Hochdruckverdichter und die Niederdruckturbine mit dem Niederdruckverdichter über jeweils eine Welle verbunden. Bei einer Gasturbine mit drei Verdichtern und drei Turbinen ist des weiteren die Mitteldruckturbine mit dem Mitteldruckverdichter über eine Welle gekoppelt. Aus dem Stand der Technik sind bereits Gasturbinen mit Generatoren bekannt, wobei die Generatoren der Erzeugung elektrischer Energie dienen. So kann zum Beispiel der Niederdruckturbine ein Generator zugeordnet sein, der im Betrieb der Gasturbine der Niederdruckturbine Leistung entnimmt und hieraus elektrische Energie erzeugt. Die von dem Generator erzeugte elektrische Energie wird dann zum Betreiben von Anbauaggregaten der Gasturbine bzw. zum Betreiben sonstiger elektrischer Einrichtungen verwendet.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.
Im Sinne der hier vorliegenden Erfindung wird vorgeschlagen, nach dem Abstellen der Gasturbine den Rotor der oder jeder Turbine für eine bestimmte Zeitdauer drehend anzutreiben, um hierdurch eine gleichmäßige Abkühlung der rotorseitigen Baugruppen des jeweiligen Turbinenrotors zu ermöglichen. Dabei wird im Sinne der Erfindung der oder jeder Generator, der im Betrieb der Gasturbine der Erzeugung elektrischer Energie dient, nach dem Abstellen der Gasturbine als Motor verwendet und demnach im Motorbetrieb betrieben. Der oder jeder Generator wandelt dann im Motorbetrieb elektrische Energie in mechanische Energie zum Antreiben des jeweiligen Turbinenrotors, wobei der jeweilige Turbinenrotor mit einer relativ geringen Drehzahl angetrieben wird. Es liegt dabei im Sinne der hier vorliegenden Erfindung, das der jeweilige Turbinenrotor mit einer Drehzahl in der Größenordnung zwischen 0,1 U/min bis 10 U/min, vorzugsweise in einer Größenordnung von 0,2 U/min bis 5 U/min, angetrieben wird.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 during 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.
Ist zum Beispiel der Niederdruckturbine einer Gasturbine ein Generator zur Erzeugung elektrischer Energie zugeordnet, so wird im Sinne der hier vorliegenden Erfindung nach dem Abstellen der Gasturbine der Generator der Niederdruckturbine im Motorbetrieb betrieben, um den Rotor der Niederdruckturbine bzw. die rotorseitigen Bauteile der Niederdruckturbine für eine bestimmte Zeitdauer anzutreiben bzw. zu drehen. Hierdurch kann eine gleichmäßige Abkühlung der rotorseitigen Baugruppen der Niederdruckturbine bewirkt werden. Unterschiedliche Temperaturen an einer Oberseite sowie einer Unterseite der rotorseitigen Baugruppen der Niederdruckturbine können vermieden werden. Ebenso ist es möglich, den Rotor einer Mitteldruckturbine sowie einer Hochdruckturbine nach dem Abstellen der Gasturbine durch einen der jeweiligen Turbine zugeordneten Generator für eine vorbestimmte Zeitdauer anzutreiben.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. 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.
Es liegt weiterhin im Sinne der hier vorliegenden Erfindung, dass nach dem Abstellen der Gasturbine zusätzlich eine Ölzirkulation im Schmiersystem der jeweiligen Turbine etabliert wird, um so eine Ölverkokung nach dem Abstellen der Gasturbine zu verhindern. Die Ölzirkulation kann zum Beispiel dadurch bewirkt werden, dass der oder jeder Generator nach dem Abstellen der Gasturbine auch eine Ölpumpe antreibt, um so die Ölzirkulation zu bewirken. Alternativ kann der durch den Generator angetriebene Turbinenrotor eine Ölzirkulation bewirken, in dem zum Beispiel dem Rotor zugeordnete Rippen im Bereich eines Lagersumpfes einer Rotorlagerung einen Pumpeffekt bewirken und so eine Ölzirkulation hervorrufen. In jedem Fall wird jedoch durch eine nach dem Abstellen der Gasturbine bewirkte Ölzirkulation eine Überhitzung des Öls verhindert und so eine Ölverkokungsgefahr reduziert.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.
Bei der Wartung bzw. Inspektion einer Gasturbine kann der oder jeder Generator ebenfalls im Motorbetrieb betrieben werden, um so zur Wartung bzw. Inspektion die rotorseitigen Baugruppen der jeweiligen Turbine zu drehen. Hierdurch kann die Inspektion von rotorseitigen Laufschaufeln, zum Beispiel beim sogenannten Boroskopieren, erleichtert werden.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)
- 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. - 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. - 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.
Applications Claiming Priority (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 true EP2027368B1 (en) | 2010-01-06 |
| EP2027368B9 EP2027368B9 (en) | 2012-01-18 |
Family
ID=37866346
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP06753264A Expired - Fee Related 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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| GB201706361D0 (en) * | 2017-04-21 | 2017-06-07 | Rolls Royce Plc | An auxiliary rotation device for a gas turbine engine and a method of cooling a rotor of a gas turbine engine using an auxiliary rotation device |
| US20180372003A1 (en) * | 2017-06-23 | 2018-12-27 | General Electric Company | Propulsion system for an aircraft |
| US20180372588A1 (en) * | 2017-06-23 | 2018-12-27 | General Electric Company | Propulsion system for an aircraft |
| US10947993B2 (en) | 2017-11-27 | 2021-03-16 | General Electric Company | Thermal gradient attenuation structure to mitigate rotor bow in turbine engine |
| US10781754B2 (en) | 2017-12-08 | 2020-09-22 | Pratt & Whitney Canada Corp. | System and method for rotor bow mitigation |
| US11549392B2 (en) | 2017-12-14 | 2023-01-10 | General Electric Company | Structure and method to mitigate rotor bow in turbine engine |
| US10760498B2 (en) | 2018-01-04 | 2020-09-01 | General Electric Company | System and method for removing rotor bow in a gas turbine engine using mechanical energy storage device |
| GB2571992A (en) * | 2018-03-16 | 2019-09-18 | Rolls Royce Plc | Gas turbine engine and method of maintaining a gas turbine engine |
| US11286855B2 (en) | 2019-03-15 | 2022-03-29 | General Electric Company | Systems and methods for operating a turbine engine |
| US11879411B2 (en) | 2022-04-07 | 2024-01-23 | General Electric Company | System and method for mitigating bowed rotor in a gas turbine engine |
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| DE524329C (en) * | 1928-08-31 | 1931-05-13 | Siemens Schuckertwerke Akt Ges | Device for slowly rotating a steam turbine shaft |
| CH349625A (en) | 1956-05-16 | 1960-10-31 | Licentia Gmbh | Device for rotating the rotor of a turbine set, which consists of a turbine with a coupled generator |
| US3793905A (en) * | 1972-08-14 | 1974-02-26 | Twin Disc Inc | Gas turbine starting and auxiliary turning mechanism |
| US4309870A (en) * | 1979-10-01 | 1982-01-12 | Carrier Corporation | Lubricating system for a turbomachine including a method of operating same |
| US4452037A (en) * | 1982-04-16 | 1984-06-05 | Avco Corporation | Air purge system for gas turbine engine |
| US4733529A (en) | 1986-09-26 | 1988-03-29 | Cef Industries, Inc. | Performance envelope extension device for a gas turbine engine |
| US4854120A (en) * | 1986-09-26 | 1989-08-08 | Cef Industries, Inc. | Performance envelope extension method for a gas turbine engine |
| CA2273944C (en) * | 1996-12-03 | 2004-07-06 | Elliott Energy Systems, Inc. | Electrical system for turbine/alternator on common shaft |
| US6031294A (en) * | 1998-01-05 | 2000-02-29 | Capstone Turbine Corporation | Turbogenerator/motor controller with ancillary energy storage/discharge |
| US6125624A (en) * | 1998-04-17 | 2000-10-03 | Pratt & Whitney Canada Corp. | Anti-coking fuel injector purging device |
| US6237322B1 (en) * | 1999-06-21 | 2001-05-29 | Pratt & Whitney Canada Corp. | Oil pump |
| WO2003038242A1 (en) * | 2001-10-30 | 2003-05-08 | Alstom Technology Ltd | Turbine unit |
| US7188475B2 (en) * | 2003-12-18 | 2007-03-13 | Honeywell International, Inc. | Starting and controlling speed of a two spool gas turbine engine |
-
2006
- 2006-06-10 EP EP06753264A patent/EP2027368B9/en not_active Expired - Fee Related
- 2006-06-10 DE DE112006003994T patent/DE112006003994A5/en not_active Withdrawn
- 2006-06-10 WO PCT/DE2006/000996 patent/WO2007140730A1/en active Application Filing
- 2006-06-10 US US12/308,211 patent/US9121309B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| WO2007140730A1 (en) | 2007-12-13 |
| DE112006003994A5 (en) | 2009-05-20 |
| US9121309B2 (en) | 2015-09-01 |
| EP2027368B9 (en) | 2012-01-18 |
| EP2027368A1 (en) | 2009-02-25 |
| US20090301053A1 (en) | 2009-12-10 |
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