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DE1041740B - Device for starting gas turbine engines - Google Patents

Device for starting gas turbine engines

Info

Publication number
DE1041740B
DE1041740B DEB41686A DEB0041686A DE1041740B DE 1041740 B DE1041740 B DE 1041740B DE B41686 A DEB41686 A DE B41686A DE B0041686 A DEB0041686 A DE B0041686A DE 1041740 B DE1041740 B DE 1041740B
Authority
DE
Germany
Prior art keywords
turbine
gas turbine
compressor
turbine engines
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.)
Pending
Application number
DEB41686A
Other languages
German (de)
Inventor
Horst W Schneider
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.)
BMW Triebwerkbau GmbH
Original Assignee
BMW Triebwerkbau 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 BMW Triebwerkbau GmbH filed Critical BMW Triebwerkbau GmbH
Priority to DEB41686A priority Critical patent/DE1041740B/en
Priority to DEB45030A priority patent/DE1045731B/en
Publication of DE1041740B publication Critical patent/DE1041740B/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F02C7/277—Mechanical drives the starter being a separate turbine

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)

Description

Vorrichtung zum Anlassen von Gasturbinentriebwerken Es ist bekannt, größere Gasturbinentriebwerke zum Zwecke des Startens mit kleineren Gasturbinentriebwerken auszurüsten, die in der Hauptsache aus einem Verdichter, einer Verdichterturbine und einer Nutz-@eistungsturbine bestehen, der zusätzlich ein Untersetzungsgetriebe nachgeschaltet ist. Für nicht ortsfeste Gasturbinentriebwerke, also für solche, die in Fahrzeugen, wie Flugzeugen, eingebaut sind, besteht teilweise die Forderung, aus eigener Kraft starten zu können, da nicht an allen Orten und zu jeder Zeit die Möglichkeit besteht, daß das Triebwerk mit fremder Hilfe, z. B. mit Preßluft, angelassen werden kann. Der wirtschaftliche, konstruktive und gewichtsmäßige Aufwand, der mit einem Starterturbinentriebwerk der eingangs beschriebenen Aufbauform verbunden ist, ist jedoch erheblich, Diesen Nachteil zu beseitigen, hat sich die Erfindung zur Aufgabe gemacht.Device for starting gas turbine engines It is known larger gas turbine engines for the purpose of starting with smaller gas turbine engines equip, which mainly consists of a compressor, a compressor turbine and a power @ power turbine, which also has a reduction gear is downstream. For non-stationary gas turbine engines, i.e. for those which are installed in vehicles, such as airplanes, there is partly the requirement, To be able to start on one's own, because not in all places and at all times the There is a possibility that the engine with outside help, z. B. with compressed air, started can be. The economic, constructive and weight-related effort that goes with is connected to a starter turbine engine of the design described above, however, is significant to eliminate this disadvantage, the invention has to Job done.

Nach der Erfindung wird als Anlasser für Gasturbinentriebwerke ein an sich bekanntes Gasturbinentriebwerk vorgeschlagen, in der Hauptsache bestehend aus Verdichter, Brennkammer und Turbine, wobei zwischen Turbine und Verdichter ein Differentialgetriebe derart angeordnet ist, daß der Verdichter über das Differentialgetriebe von der Turbine angetrieben wird und an dem verbleibenden freien Abtrieb des Differentialgetriebes die Differenzleistung zwischen Verdichter und Turbine als Nutzleistung abnehmbar ist.According to the invention is used as a starter for gas turbine engines proposed per se known gas turbine engine, consisting in the main Compressor, combustion chamber and turbine, with one between the turbine and the compressor Differential gear is arranged such that the compressor via the differential gear is driven by the turbine and on the remaining free output of the differential gear the differential power between the compressor and the turbine can be removed as useful power is.

Die vorschlagsgemäße Verwendung des Gasturbinentriebwerkes als Anlasser bringt vor allen Dingen den Vorteil, daß es hierbei unter Last - also ohne von dem Hauptturbinentriebwerk so lange abgekuppelt zu sein, bis es selbst auf Drehzahl gekommen ist - hochfahren kann. Es kommen dadurch komplizierte Zusatzeinrichtungen in Fortfall. Außerdem kann beim Startvorgang das Starterturbinentriebwerk, ohne seine eigene Turbine zu überdrehen, bis auf eine höhere Drehzahl des anzulassenden Haupttriebwerkes nachschieben, und zwar so lange, bis sein Prozeß zusammenbricht, d. h., das Startertriebwerk kann so geregelt werden, daß bei konstanter maximaler Drehzahl der Turbine die Abtriebsdrehzahl (die Drehzahl, mit der die Abtriebswelle den Verdichter des Hauptturbinentriebwerkes antreibt) unter gleichzeitiger Absinkung der Verdichterdrehzahl und Leistung weiter ansteigt.The proposed use of the gas turbine engine as a starter Above all, it has the advantage that it is under load - that is, without the Main turbine engine to be decoupled until it is up to speed by itself has come - can boot up. This results in complicated additional equipment in failure. In addition, the starter turbine engine can, without over-revving its own turbine, up to a higher speed of the one to be started Push in the main engine until its process collapses, d. That is, the starter engine can be controlled so that at a constant maximum Speed of the turbine the output speed (the speed at which the output shaft drives the compressor of the main turbine engine) with simultaneous lowering the compressor speed and performance continue to increase.

Der Gegenstand der Erfindung liegt nicht in der Ausbildung und in dem Aufbau des Startergasturbinentrieb@werkes selbst, das für sich betrachtet bekannt ist, sondern die Erfindung liegt vielmehr ausschließlich in der Verwendung dieses Triebwerkes als Anlaßaggregat für Gasturbinentriebwerke.The object of the invention is not in the training and in the structure of the starter gas turbine engine itself, which is known for itself is, but rather the invention lies solely in the use of this Engine as a starting unit for gas turbine engines.

Claims (1)

PATENTANSPRUCH: Zum Anlassen von Gasturbinentriebwerken bestimmtes Gasturbinentriebwerk, dadurch gekennzeichnet, daß das Anlassertriebwerk in an sich bekannter Weise hauptsächlich aus Verdichter, Brennkammer und Turbine besteht, wobei antriebsmäßig zwischen Turbine und Verdichter ein Differentialgetriebe derart angeordnet ist, daß der Verdichter über das Differentialgetriebe von der Turbine angetrieben wird und an dem verbleibenden freien Abtrieb des Differentialgetriebes die Differenzleistung zwischen Verdichter und Turbine als Nutzleistung abnehmbar ist.PATENT CLAIM: Certain for starting gas turbine engines Gas turbine engine, characterized in that the starter engine in itself known way consists mainly of compressor, combustion chamber and turbine, wherein A differential gear is arranged in terms of drive between the turbine and the compressor in this way is that the compressor is driven by the turbine via the differential gear and on the remaining free output of the differential gear, the differential power between the compressor and turbine as useful power can be removed.
DEB41686A 1954-08-10 1954-08-10 Device for starting gas turbine engines Pending DE1041740B (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DEB41686A DE1041740B (en) 1954-08-10 1954-08-10 Device for starting gas turbine engines
DEB45030A DE1045731B (en) 1954-08-10 1956-09-08 Arrangement of a starter gas turbine engine in a gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DEB41686A DE1041740B (en) 1954-08-10 1954-08-10 Device for starting gas turbine engines
DEB45030A DE1045731B (en) 1954-08-10 1956-09-08 Arrangement of a starter gas turbine engine in a gas turbine engine

Publications (1)

Publication Number Publication Date
DE1041740B true DE1041740B (en) 1958-10-23

Family

ID=62596991

Family Applications (2)

Application Number Title Priority Date Filing Date
DEB41686A Pending DE1041740B (en) 1954-08-10 1954-08-10 Device for starting gas turbine engines
DEB45030A Pending DE1045731B (en) 1954-08-10 1956-09-08 Arrangement of a starter gas turbine engine in a gas turbine engine

Family Applications After (1)

Application Number Title Priority Date Filing Date
DEB45030A Pending DE1045731B (en) 1954-08-10 1956-09-08 Arrangement of a starter gas turbine engine in a gas turbine engine

Country Status (1)

Country Link
DE (2) DE1041740B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1259140B (en) * 1963-05-03 1968-01-18 Plessey Uk Ltd Turning device for internal combustion engines
DE1264868B (en) * 1962-10-11 1968-03-28 Bendix Corp Starter for gas turbine engines

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2652685A (en) * 1948-05-13 1953-09-22 United Aricraft Corp Starting device for compressorturbine units

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1264868B (en) * 1962-10-11 1968-03-28 Bendix Corp Starter for gas turbine engines
DE1259140B (en) * 1963-05-03 1968-01-18 Plessey Uk Ltd Turning device for internal combustion engines

Also Published As

Publication number Publication date
DE1045731B (en) 1958-12-04

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