DE102006023246A1 - Turbo engine e.g. aircraft engine, has fan-rotor driven into flow channel, another rotor arranged downstream to former rotor, and booster-compressor with booster-rotors that are connected with respective fan-rotors in rotating manner - Google Patents
Turbo engine e.g. aircraft engine, has fan-rotor driven into flow channel, another rotor arranged downstream to former rotor, and booster-compressor with booster-rotors that are connected with respective fan-rotors in rotating manner Download PDFInfo
- Publication number
- DE102006023246A1 DE102006023246A1 DE200610023246 DE102006023246A DE102006023246A1 DE 102006023246 A1 DE102006023246 A1 DE 102006023246A1 DE 200610023246 DE200610023246 DE 200610023246 DE 102006023246 A DE102006023246 A DE 102006023246A DE 102006023246 A1 DE102006023246 A1 DE 102006023246A1
- Authority
- DE
- Germany
- Prior art keywords
- rotor
- fan
- booster
- rotors
- compressor
- 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.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/068—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type being characterised by a short axial length relative to the diameter
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
Abstract
Description
Die Erfindung betrifft ein Turbotriebwerk mit
- – einem in einem Strömungskanal rotierenden angetriebenen ersten Fan-Rotor,
- – einem stromab von dem ersten Fan-Rotor angeordneten zweiten Fan-Rotor, der gegensinnig zu dem ersten Fan-Rotor angetrieben ist,
- – und einem zwischen den beiden Fan-Rotoren angeordneten Booster-Verdichter mit einem ersten Booster-Rotor, der mitdrehend mit dem ersten Fan-Rotor verbunden ist,
- A driven first fan rotor rotating in a flow channel,
- A second fan rotor arranged downstream of the first fan rotor and driven in opposite directions to the first fan rotor,
- And a booster compressor arranged between the two fan rotors with a first booster rotor which is connected in a co-rotating manner with the first fan rotor,
Moderne Flugtriebwerke besitzen einen Verdichter, der aus einem oder mehreren Fan-Rotoren bestehen kann und die einströmende Luft verdichtet. Der größte Teil der Luft wird durch den sogenannten Bypass als schuberzeugender Luftstrahl nach hinten ausgeschoben. Der innere Rest der Luft wird dem Kerntriebwerk (Core) zugeführt. Dort wird die Luft im Hochdruckverdichter weiter verdichtet und einer Brennkammer zugeführt. Das Verdichtungsvermögen des Hochdruckverdichters reicht oft nicht aus, so dass unmittelbar nach dem Eintritt in das Kerntriebwerk ein Booster-Verdichter zur weiteren Verdichtung der Verbrennungsluft angeordnet ist. Die Fan-Rotoren und der Booster-Verdichter werden durch Gasturbinen angetrieben. Typische Ausführungen von Triebwerken haben zwei oder drei Wellen, wobei der erste Fan-Rotor mit einer inneren Welle angetrieben ist, während der zweite Fan-Rotor von einer koaxial um die innere Welle herum angeordneten äußeren Hohlwelle angetrieben ist.modern Aero engines have a compressor that consists of one or more Fan rotors can exist and the incoming air is compressed. Of the biggest part The air is created by the so-called bypass as thrust-generating Air jet pushed out to the rear. The inner remainder of the air becomes fed to the core engine (Core). There, the air in the high-pressure compressor is further compressed and fed to a combustion chamber. The compaction power Of the high pressure compressor is often not enough, so that immediately after entering the core engine a booster compressor for further compression of the combustion air is arranged. The fan rotors and the booster compressor are powered by gas turbines. Typical designs of engines have two or three shafts, with the first fan rotor is driven with an inner shaft while the second fan rotor from a coaxially arranged around the inner shaft outer hollow shaft is driven.
Ein
Turbotriebwerk, das in
Der Oberbegriff des Patentanspruchs 1 geht aus von einem Turbotriebwerk nach US 2005/0241291 A1. Dieses Triebwerk weist innerhalb eines Strömungskanals zwei hintereinander angeordnete Fan-Rotoren auf, die gegenläufig angetrieben sein können. Zwischen beiden Fan-Rotoren befindet sich ein Booster-Verdichter. Dieser besteht aus einem mit dem vorderen Fan-Rotor drehfest gekoppelten Flügelrad und einem mehrflügeligen Stator. Auch hierbei ergibt sich die Schwierigkeit, dass der Booster-Verdichter nur eine geringe Verdichtung bewirken kann, weil die Drehzahl durch den Fan-Rotor, der einen großen Durchmesser hat, begrenzt ist.Of the The preamble of claim 1 is based on a turbo engine according to US 2005/0241291 A1. This engine points within a flow channel two successively arranged fan rotors, which are driven in opposite directions can. Between both fan rotors there is a booster compressor. This consists of a non-rotatably coupled to the front fan rotor impeller and a multi-leaf Stator. Again, there is the difficulty that the booster compressor only a small compression can cause, because the speed through the fan rotor, which is a big one Diameter is limited.
Der Vorteil gegenläufiger Gebläse (und Verdichter) ist die Möglichkeit der Aufteilung der Energieübertragung auf zwei Schaufelreihen. Zur Erzielung einer hohen Verdichtung muss also nicht notwendigerweise die Anzahl der Schaufelreihen vergrößert werden. Auf diese Weise kann der Verdichter mit kürzerer Bauform realisiert werden. Bei gegenläufigen Fan-Rotoren tritt das Problem einer höheren Lärmabstrahlung auf.Of the Advantage opposite fan (and compressors) is the possibility the distribution of energy transfer on two rows of blades. To achieve a high compression must So not necessarily the number of blade rows are increased. In this way, the compressor can be realized with a shorter design. With counter-rotating fan rotors occurs the problem of higher noise emission on.
Der Erfindung liegt die Aufgabe zugrunde, ein Turbotriebwerk zu schaffen, das infolge einer hohen Verdichtung des kurzflügeligen Booster-Verdichters eine hohe Leistung liefert, wobei andererseits der Booster-Verdichter trotz einer kurzen Bauform kein zusätzliches Getriebe erfordert.Of the Invention has for its object to provide a turbo engine, This is due to a high compression of the short-wing booster compressor high performance, on the other hand, the booster compressor despite a short design no additional gear required.
Das erfindungsgemäße Turbotriebwerk ist durch den Patentanspruch 1 bezeichnet. Bei ihm weist der Booster-Verdichter zusätzlich zu dem ersten Booster-Rotor einen zweiten Booster-Rotor auf, der mitdrehend mit dem zweiten Fan-Rotor verbunden ist. Auf diese Weise rotieren der zweite Booster-Rotor und der zweite Fan-Rotor gemeinsam mit der gleichen relativ niedrigen Drehzahl. Sowohl die beiden Fan-Rotoren rotieren gegenläufig zueinander als auch die beiden Booster-Rotoren. Dadurch wird die Verdichtungsleistung des Booster-Verdichters wesentlich erhöht, ohne dessen Abmessungen zu vergrößern. Mit der gleichen Anzahl von Schaufelreihen kann eine deutliche Steigerung des Druckverhältnisses des Booster-Verdichters erreicht werden.The Turbo engine according to the invention is designated by the patent claim 1. In him, the booster compressor points additionally to the first booster rotor on a second booster rotor, the co-rotating with the second fan rotor is connected. In this way The second booster rotor and the second fan rotor rotate together with the same relatively low speed. Both the two fan rotors rotate in opposite directions each other as well as the two booster rotors. This will be the Compaction performance of the booster compressor essential elevated, without enlarging its dimensions. With The same number of rows of blades can be a significant increase the pressure ratio of the booster compressor can be achieved.
Gemäß einer bevorzugten Ausführungsform der Erfindung ist vorgesehen, dass der zweite Fan-Rotor mit einem rohrförmigen Spinner verbunden ist, der an seiner Innenseite den zweiten Booster-Rotor aufweist. Der rotierende Spinner teilt den in den Strömungskanal einströmenden Luftstrom in einen äußeren Bypass-Strom und einen inneren Hauptstrom. Gleichzeitig dient er als Träger für den zweiten Booster-Rotor. Hierdurch entsteht eine kompakte und stabile Bauform.According to one preferred embodiment of Invention is provided that the second fan rotor with a tubular spinner connected to the inside, the second booster rotor having. The rotating spinner divides the into the flow channel incoming Air flow into an external bypass flow and an inner mainstream. At the same time he serves as a carrier for the second Booster rotor. This creates a compact and stable design.
Vorteilhaft ist der Booster-Verdichter zwischen den beiden Fan-Rotoren angeordnet. Hierdurch wird erreicht, dass die Fan-Rotoren einen relativ großen Abstand haben können, wodurch die Lärmerzeugung des Turbotriebwerks reduziert wird.Advantageous the booster compressor is located between the two fan rotors. This ensures that the fan rotors a relatively large distance can have, causing the noise generation of the turbo engine is reduced.
Bei einer bevorzugten Ausführungsform der Erfindung ist der erste Fan-Rotor an einem Nabenkörper befestigt, der mit einer rotierenden ersten Welle verbunden ist, und der zweite Fanrotor ist an einer zweiten Welle befestigt, die die erste Welle koaxial umgibt.at a preferred embodiment invention, the first fan rotor is attached to a hub body, which is connected to a rotating first shaft, and the second Fan rotor is attached to a second shaft, which is the first shaft Coaxially surrounds.
Im Folgenden wird unter Bezugnahme auf die einzige Figur der Zeichnung ein Ausführungsbeispiel der Erfindung näher erläutert.in the The following will be made with reference to the sole figure of the drawing an embodiment closer to the invention explained.
In der Zeichnung ist ein Längsschnitt durch ein erfindungsgemäßes Turbotriebwerk in seinem prinzipiellen Aufbau dargestellt.In The drawing is a longitudinal section by a turbocharger according to the invention shown in its basic structure.
Das
dargestellte Turbotriebwerk ist ein Flugzeugtriebwerk, von dem hier
nur der vordere Teil mit den Fan-Rotoren und dem Booster-Verdichter
gezeigt ist. Der rückwärtige Teil,
der einen Hochdruckverdichter, eine Brennkammer sowie zwei Niederdruckturbinen
enthält,
ist nicht dargestellt. Der grundsätzliche Aufbau des Turbotriebwerks
entspricht demjenigen von
Das
Turbotriebwerk weist ein ringförmiges Gehäuse
Die
zweite Welle
Mit
der zweiten Welle
Zwischen
dem ersten Fan-Rotor
Im
Betrieb rotieren der erste Fan-Rotor
Der
Spinner
Claims (4)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200610023246 DE102006023246A1 (en) | 2006-05-18 | 2006-05-18 | Turbo engine e.g. aircraft engine, has fan-rotor driven into flow channel, another rotor arranged downstream to former rotor, and booster-compressor with booster-rotors that are connected with respective fan-rotors in rotating manner |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200610023246 DE102006023246A1 (en) | 2006-05-18 | 2006-05-18 | Turbo engine e.g. aircraft engine, has fan-rotor driven into flow channel, another rotor arranged downstream to former rotor, and booster-compressor with booster-rotors that are connected with respective fan-rotors in rotating manner |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102006023246A1 true DE102006023246A1 (en) | 2007-11-22 |
Family
ID=38607932
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE200610023246 Withdrawn DE102006023246A1 (en) | 2006-05-18 | 2006-05-18 | Turbo engine e.g. aircraft engine, has fan-rotor driven into flow channel, another rotor arranged downstream to former rotor, and booster-compressor with booster-rotors that are connected with respective fan-rotors in rotating manner |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE102006023246A1 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102008005163A1 (en) | 2008-01-19 | 2009-08-20 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Aircraft engine for use turbofan engine for civilian application, has propane fan stage with encased propane rotors, whose rotor blades are surrounded by co-rotating shell, where rotors are made from fiber-reinforced plastic |
WO2010059321A3 (en) * | 2008-11-21 | 2011-04-14 | General Electric Company | Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes |
WO2013029584A1 (en) | 2011-08-27 | 2013-03-07 | Mtu Aero Engines Gmbh | Method for manufacturing, repairing and/or exchanging a rotor/stator combination system, and a rotor/stator combination system manufactured in accordance wih the method |
DE102011084360A1 (en) * | 2011-10-12 | 2013-04-18 | Rolls-Royce Deutschland Ltd & Co Kg | Flow working machine for use in aircraft engine, has main rotor disk or drum driven by main shaft, and auxiliary rotor disk or drum driven by auxiliary shaft, where shafts comprise different rotational speed and/or rotational direction |
-
2006
- 2006-05-18 DE DE200610023246 patent/DE102006023246A1/en not_active Withdrawn
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102008005163A1 (en) | 2008-01-19 | 2009-08-20 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Aircraft engine for use turbofan engine for civilian application, has propane fan stage with encased propane rotors, whose rotor blades are surrounded by co-rotating shell, where rotors are made from fiber-reinforced plastic |
DE102008005163B4 (en) * | 2008-01-19 | 2009-12-03 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Aircraft engine |
WO2010059321A3 (en) * | 2008-11-21 | 2011-04-14 | General Electric Company | Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes |
US8166748B2 (en) | 2008-11-21 | 2012-05-01 | General Electric Company | Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes |
WO2013029584A1 (en) | 2011-08-27 | 2013-03-07 | Mtu Aero Engines Gmbh | Method for manufacturing, repairing and/or exchanging a rotor/stator combination system, and a rotor/stator combination system manufactured in accordance wih the method |
DE102011084360A1 (en) * | 2011-10-12 | 2013-04-18 | Rolls-Royce Deutschland Ltd & Co Kg | Flow working machine for use in aircraft engine, has main rotor disk or drum driven by main shaft, and auxiliary rotor disk or drum driven by auxiliary shaft, where shafts comprise different rotational speed and/or rotational direction |
DE102011084360B4 (en) * | 2011-10-12 | 2015-07-02 | Rolls-Royce Deutschland Ltd & Co Kg | Turbomachine |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
OP8 | Request for examination as to paragraph 44 patent law | ||
8139 | Disposal/non-payment of the annual fee |