DE1045731B - Arrangement of a starter gas turbine engine in a gas turbine engine - Google Patents

Arrangement of a starter gas turbine engine in a gas turbine engine

Info

Publication number
DE1045731B
DE1045731B DEB45030A DEB0045030A DE1045731B DE 1045731 B DE1045731 B DE 1045731B DE B45030 A DEB45030 A DE B45030A DE B0045030 A DEB0045030 A DE B0045030A DE 1045731 B DE1045731 B DE 1045731B
Authority
DE
Germany
Prior art keywords
compressor
gas turbine
turbine
engine
turbine 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
DEB45030A
Other languages
German (de)
Inventor
Horst 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
Priority to DEB41686A priority Critical patent/DE1041740B/en
Application filed by BMW Triebwerkbau GmbH filed Critical BMW Triebwerkbau GmbH
Priority to DEB45030A priority patent/DE1045731B/en
Publication of DE1045731B publication Critical patent/DE1045731B/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)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Description

Anordnung eines Startergasturbinentriebwerkes in einem Gasturbinentriebwerk Die Patentanmeldung B 41686 Ia/46f hat eine Einrichtung zum Anlassen von Gasturbinentriebwerken zum Gegenstand, das gekennzeichnet ist durch ein an sich bekanntes Gasturbinentriebwerk, in der Hauptsache bestehend aus Verdichter, Brennkammer und Turbine, 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 für den Antrieb des Verdichters des Haupttriebwerkes beim Starten abnehmbar ist.Arrangement of a starter gas turbine engine in a gas turbine engine The patent application B 41686 Ia / 46f has a device for starting gas turbine engines to the subject, which is characterized by a gas turbine engine known per se, Mainly consisting of a compressor, combustion chamber and turbine, whereby in terms of drive a differential gear is arranged between the turbine and the compressor in such a way that that the compressor is driven by the turbine via the differential gear and the differential power at the remaining free output of the differential gear between compressor and turbine as useful power for driving the compressor the main engine can be removed when starting.

Die Zusatzerfindung befaßt sich mit der räumlichen Anordnung eines derartigen Startertriebwerkes innerhalb des Haupttriebwerkes. Hierbei ist es bereits bekannt, das zum Anlassen benutzte Triebwerk in der Nabe des Haupttriebwerkes anzuordnen.The additional invention deals with the spatial arrangement of a such starter engine within the main engine. Here it is already known to arrange the engine used for starting in the hub of the main engine.

Die Eigenheiten des zum Anlassen vorgeschlagenen Gasturbinentriebwerkes, bei dem ein Differentialgetriebe zwischen Verdichter und Turbine vorgesehen ist, ergeben für den Einbau eine besonders günstige konstruktive Lösung in bezug auf raumsparende und aerodynamische Probleme. Die Erfindung schlägt vor, den Einbau des Startertriebwerkes in die Nabe des Haupttriebwerkes derart vorzunehmen, daß die Turbine vorn liegt und über den Nabenkopf die Abgase ausbläst, der Verdichter sich in der Mitte befindet und über den Außenumfang der Nabe Frischluft ansaugt und das Differentialgetriebe im hinteren Teil der Nabe vor dem Verdichter des Hauptturbinentriebwerkes liegt, wobei zwischen dem Differentialgetriebe und dem Verdichter eine Überholkupplung geschaltet ist.The peculiarities of the gas turbine engine proposed for starting, in which a differential gear is provided between the compressor and the turbine, result in a particularly favorable structural solution for the installation with respect to space-saving and aerodynamic problems. The invention proposes the installation of the starter engine in the hub of the main engine in such a way that the turbine is in front and blows out the exhaust gases via the hub head, the compressor is located in the middle and draws in fresh air over the outer circumference of the hub and the differential gear in the rear of the hub in front of the compressor of the main turbine engine is, with an overrunning clutch between the differential gear and the compressor is switched.

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung dargestellt, und zwar veranschaulicht die Zeichnung ein Hauptgasturbinentriebwerk mit einem in seiner Nabe eingebauten Startergasturbinentriebwerk.In the drawing, an embodiment of the invention is shown, namely, the drawing illustrates a main gas turbine engine with an in starter gas turbine engine built into its hub.

In der Nabel des Hauptgasturbinentriebwerkes 2 ist eine Startergasturbine, bestehend aus einem Verdichter 3, Turbine 4, Brennkammer 11 und Differentialgetriebe 5, eingebaut. Vom Differentialgetriebe 5 geht der Nutzleistungsantrieb 6 über eine Überholkupplung 7 auf den Verdichter bzw. auf die erste Verdichterstufe 8 des Haupttriebwerkes 2. Der Lufteinlaß 9 für den Verdichter 3 liegt am Außenumfang der abe 1. Der Lufteintritt 10 für den Axialverdichter 8 des Haupttriebwerkes 2 liegt in üblicher Weise ringförmig um die Nabe 1. Die Turbine 4 des Startertriebwerkes bläst ihre Abgase zentral durch den Kopf der Nabe 1.In the navel of the main gas turbine engine 2 is a starter gas turbine, consisting of a compressor 3, turbine 4, combustion chamber 11 and differential gear 5, built-in. The utility drive 6 goes from the differential gear 5 via a Overrunning clutch 7 on the compressor or on the first compressor stage 8 of the main engine 2. The air inlet 9 for the compressor 3 is on the outer circumference of the abe 1. The air inlet 10 for the axial compressor 8 of the main engine 2 is in the usual way annular around the hub 1. The turbine 4 of the starter engine blows its exhaust gases through centrally the head of the hub 1.

Claims (1)

PATENTANSPRUCH: Anordnung eines Startergasturbinentriebwerkes, hauptsächlich bestehend aus Verdichter, Brennkammer und Turbine, in einem Hauptgasturbinentriebwerk, 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 für den Antrieb des Verdichters des Haupttriebwerkes beim Starten abnehmbar ist, nach Patentanmeldung B 41686 Ia/46f, dadurch gekennzeichnet, daß das Startergasturbinentriebwerk derart in der Nabe (1) des Haupttriebwerkes (2) angeordnet ist, daß die Turbine (4) vorn liegt und über den Nabenkopf die Abgase ausbläst, der Verdichter (3) sich in der Mitte befindet und über den Außenumfang der Nabe (1) Luft ansaugt und das Differentialgetriebe (5) im hinteren Teil der Nabe (1) vor dem Verdichter (8) des Haupttriebwerkes (2) liegt, wobei zwischen dem Differentialgetriebe (5) und dem Verdichter (8) eine Überholkupplung (7) geschaltet ist. In Betracht gezogene Druckschriften: USA.-Patentschrift Nr. 2 652 685; The Aeroplane, Bd. 89, 1955, S. 574, 575, 951 bis 953, und Bd. 88, 1955, S. 742, 743. PATENT CLAIM: Arrangement of a starter gas turbine engine, mainly consisting of a compressor, combustion chamber and turbine, in a main gas turbine engine, a differential gear being arranged between the turbine and the compressor in terms of drive such 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 the turbine can be removed as useful power for driving the compressor of the main engine when starting, according to patent application B 41686 Ia / 46f, characterized in that the starter gas turbine engine is arranged in the hub (1) of the main engine (2) in such a way that the turbine (4) is at the front and blows out the exhaust gases via the hub head, the compressor (3) is in the middle and sucks in air over the outer circumference of the hub (1) and the differential gear (5) in the rear part of the hub (1) in front of the compressor (8) of the main engine kes (2), an overrunning clutch (7) being connected between the differential gear (5) and the compressor (8). References considered: U.S. Patent No. 2,652,685; The Airplane, Vol. 89, 1955, pp. 574, 575, 951 to 953, and Vol. 88, 1955, pp. 742, 743.
DEB45030A 1954-08-10 1956-09-08 Arrangement of a starter gas turbine engine in a gas turbine engine Pending DE1045731B (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
DE1045731B true DE1045731B (en) 1958-12-04

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 Before (1)

Application Number Title Priority Date Filing Date
DEB41686A Pending DE1041740B (en) 1954-08-10 1954-08-10 Device for starting gas turbine engines

Country Status (1)

Country Link
DE (2) DE1041740B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1072485A (en) * 1963-05-03 1967-06-14 Plessey Uk Ltd Improvements in or relating to engine-starter and auxiliary drive systems

Citations (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

Patent Citations (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

Also Published As

Publication number Publication date
DE1041740B (en) 1958-10-23

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