DE102009042242A1 - Turbofan driving gear has core duct and bypass duct and guide vane collar that is arranged in bypass duct, where selective positioning of supporting struts or bifurcations is determined in certain relation to guide vanes - Google Patents
Turbofan driving gear has core duct and bypass duct and guide vane collar that is arranged in bypass duct, where selective positioning of supporting struts or bifurcations is determined in certain relation to guide vanes Download PDFInfo
- Publication number
- DE102009042242A1 DE102009042242A1 DE200910042242 DE102009042242A DE102009042242A1 DE 102009042242 A1 DE102009042242 A1 DE 102009042242A1 DE 200910042242 DE200910042242 DE 200910042242 DE 102009042242 A DE102009042242 A DE 102009042242A DE 102009042242 A1 DE102009042242 A1 DE 102009042242A1
- Authority
- DE
- Germany
- Prior art keywords
- vane
- bifurcations
- bypass duct
- bifurcation
- vanes
- 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.)
- Ceased
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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
- F02K3/06—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 front fan
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Die Erfindung betrifft ein Turbofantriebwerk mit einem Kern- und einem Nebenstromkanal und einem im Nebenstromkanal angeordneten Leitschaufelkranz aus in Umfangsrichtung im Abstand angeordneten, eine Druck- und eine Saugseite aufweisenden Leitschaufeln sowie stromab von diesen angeordneten, aerodynamisch geformten Stützstreben und/oder Bifurkationen.The invention relates to a turbofan engine with a core and a bypass duct and arranged in the bypass duct vane from circumferentially spaced, a pressure and a suction side having vanes and arranged downstream of these, aerodynamically shaped struts and / or bifurcations.
Turbofantriebwerke weisen hinter dem an der Lufteintrittsseite befindlichen Fan einen Strömungsteiler auf, der den vom Fan erzeugten Luftstrom in einen Kernluftstrom und einen Nebenluftstrom aufteilt. Der Nebenluftstrom strömt in einem von einer inneren, einen Kernstromkanal begrenzenden Seitenwand und einer sich auf dieser abstützenden Triebwerksverkleidung gebildeten Nebenstromkanal. Die Abstützung der Triebwerksverkleidung auf der inneren Seitenwand oder Trennwand erfolgt zum einen durch die Leitschaufeln eines dem Fan im Nebenstromkanal nachgeschalteten Leitschaufelkranzes, dessen wesentliche Funktion in der Entfernung des Dralls aus der vom Fan erzeugten Strömung besteht, sowie durch – in Abhängigkeit vom Triebwerkstyp – stromab vom Leitschaufelkranz gegebenenfalls angeordnete Stützstreben. Darüber hinaus ist im Nebenstromkanal stromab vom Leitschaufelkranz oder von den Stützstreben mindestens ein als Bifurkation bezeichnetes Verkleidungselement, durch das die Leitungen zur Versorgung des Triebwerks und/oder des Flugzeugs geführt sind, angeordnet. Die Bifurkationen dienen zur aerodynamischen Umströmung der Versorgungsleitungen, um durch Vibrationen bedingte mechanische Auswirkungen sowie Verwirbelungen und Druckverluste im Nebenstromkanal gering zu halten. Die im Nebenstromkanal vorhandenen Einbauten sind zu einem erheblichen Teil für die dort auftretenden Druckverluste und den damit verbundenen erhöhten Treibstoffbedarf des Triebwerks verantwortlich. Darüber hinaus erzeugen diese Einbauten in Umfangsrichtung des Nebenstromkanals statische Druckschwankungen, die auf den Fan zurückwirken und dessen Betriebstabilität beeinträchtigen. Die demzufolge erforderliche stabilere Auslegung des Fans ist mit einer Erhöhung des Treibstoffsbedarfs und einer Verringerung des Wirkungsgrades des Triebwerks verbunden. Um die Aufstauwirkung der Einbauten und die dadurch bedingten Druckschwankungen zu beseitigen, wurde bereits vorgeschlagen, den Strömungsquerschnitt im Nebenstromkanal im Bereich der Vorderkanten der Stützstreben und Bifurkationen in axialer Richtung und in Umfangsrichtung allmählich zu erweitern.Turbofan engines have, behind the fan located on the air inlet side, a flow divider which divides the air flow generated by the fan into a core air flow and a secondary air flow. The secondary air flow flows in a sidewall formed by an inner, a core flow channel and a side wall channel formed on this supporting engine cowling. The support of the engine cowling on the inner side wall or partition takes place on the one hand by the vanes of the fan in the bypass duct downstream vane ring whose essential function is the removal of the swirl from the flow generated by the fan, and - depending on the type of engine - downstream of Guide vane optionally arranged support struts. In addition, in the bypass duct downstream of the vane ring or of the support struts, at least one cladding element, referred to as a bifurcation, through which the ducts are led to supply the engine and / or the aircraft is arranged. The bifurcations serve to aerodynamically flow around the supply lines in order to minimize vibration-induced mechanical effects and turbulences and pressure losses in the bypass channel. The internals present in the bypass duct are responsible to a considerable extent for the pressure losses occurring there and the associated increased fuel requirements of the engine. In addition, these internals produce in the circumferential direction of the bypass channel static pressure fluctuations, which act back on the fan and affect its operational stability. The consequently more stable design of the fan is associated with an increase in fuel consumption and a reduction in the efficiency of the engine. In order to eliminate the accumulation effect of the internals and the consequent pressure fluctuations, it has been proposed to gradually expand the flow cross-section in the bypass duct in the region of the leading edges of the support struts and bifurcations in the axial direction and in the circumferential direction.
Der Erfindung liegt die Aufgabe zugrunde, die durch die Bifurkationen und Stützstreben bewirkten Druckverluste und die auf den Fan zurückwirkenden Druckschwankungen signifikant zu verringern und dadurch die Betriebsstabilität und den Wirkungsgrad des Fans zu verbessern und den Treibstoffverbrauch zu senken.The invention has for its object to significantly reduce the pressure losses caused by the bifurcations and struts and the pressure fluctuations acting back on the fan and thereby improve the operating stability and efficiency of the fan and to reduce fuel consumption.
Erfindungsgemäß wird die Aufgabe mit einem gemäß den Merkmalen des Patentanspruchs 1 ausgebildeten Nebenstromkanal gelöst. Vorteilhafte Weiterbildungen der Erfindung sind Gegenstand der Unteransprüche.According to the invention the object is achieved with a trained according to the features of
Der Grundgedanke der Erfindung besteht in einer in Bezug auf die Anordnung und Ausbildung der Leitschaufeln vorgegebenen, speziellen Positionierung der im Nebenstrom aerodynamisch angeordneten Stützstreben und/oder Bifurkationen. Das heißt, die Stützstreben und/oder Bifurkationen sind im Verhältnis zu den jeweils stromauf liegenden Leitschaufeln so positioniert, dass sich die betreffende Stützstrebe oder Bifurkation jeweils im Bereich der an der Druckseite einer Leitschaufel erzeugten verlustminimalsten Strömung befindet und von dieser Strömung achsparallel angeströmt oder umströmt wird. Die nahe der Saugseite einer benachbarten Leitschaufel erzeugte verluststärkste Strömung wird hingegen an der Stützstrebe oder Bifurkation vorbeigeführt. Aufgrund dieser speziellen Zuordnung der Stützstreben und Bifurkationen zu den Leitschaufeln bzw. deren Einbindung in den hinter dem Leitschaufelkranz austretenden Nebenstrom können die Druckverluste im Nebenstromkanal minimiert sowie die in Umfangsrichtung erzeugten statischen Druckschwankungen, die auf den Fan zurückwirken und dessen Betriebsstabilität beeinträchtigen, verringert werden, so dass der Treibstoffverbrauch des Triebwerks gesenkt und letztlich dessen Wirkungsgrad verbessert werden kann.The basic idea of the invention consists in a specific positioning of the support struts and / or bifurcations arranged aerodynamically in the secondary flow in relation to the arrangement and design of the guide vanes. That is, the support struts and / or bifurcations are positioned in relation to the respective upstream vanes so that the respective support strut or bifurcation is in each case in the region of the loss-minimized flow generated on the pressure side of a guide vane and is impinged on or flowed around axially parallel to this flow , On the other hand, the most lossy flow generated near the suction side of an adjacent guide vane is guided past the support strut or bifurcation. Due to this special assignment of the support struts and bifurcations to the guide vanes or their integration in the emerging behind the vane side flow, the pressure losses in the bypass channel can be minimized and the generated in the circumferential direction static pressure fluctuations, which act on the fan and affect its operating stability, so that the fuel consumption of the engine can be lowered and ultimately its efficiency can be improved.
In vorteilhafter Weiterbildung der Erfindung befindet sich die Vorderkante der jeweiligen Stützstrebe oder Bifurkation in einer um das Maß 0,75 S bis 1 S von der Saugseite weg und zur Druckseite der benachbarten Leitschaufel hin festgelegten Position. Das heißt, die Vorderkante der Stützstrebe oder Bifurkation liegt maximal in Höhe der Hinterkante bzw. an oder nahe der Druckseite einer Leitschaufel und ist mindestens um das Maß 0,75 S von der Saugseite der benachbarten Leitschaufel entfernt. Hierbei ist S der Abstand zwischen den Hinterkanten der beiden aufeinander folgenden Leitschaufeln.In an advantageous development of the invention, the front edge of the respective support strut or bifurcation is located in a position determined by the dimension 0.75 S to 1 S from the suction side and toward the pressure side of the adjacent guide blade. That is, the leading edge of the support strut or bifurcation lies maximally at the level of the trailing edge or at or near the pressure side of a guide vane and is at least 0.75 S from the suction side of the adjacent vane. Here, S is the distance between the trailing edges of the two successive vanes.
Gemäß einem weiteren Merkmal der Erfindung haben einzelne Leitschaufeln eine größere Sehnenlänge und eine dadurch verbesserte Stützwirkung. Auch in diesem Fall ist die Vorderkante einer stromab angeordneten Stützstrebe oder Bifurkation um das Maß 0,75 S bis 1 S von der Saugseite der langen Leitschaufel weg zur Druckseite der folgenden – kurzen – Leitschaufel hin positioniert.According to a further feature of the invention, individual vanes have a greater chord length and thereby improved support effect. Also in this case, the leading edge of a downstream strut or bifurcation is positioned 0.75 S to 1 S away from the suction side of the long vane toward the pressure side of the following short vane.
Ein Ausführungsbeispiel der Erfindung wird anhand der Zeichnung näher erläutert. Es zeigen:An embodiment of the invention will be explained in more detail with reference to the drawing. Show it:
Gemäß der in
In
BezugszeichenlisteLIST OF REFERENCE NUMBERS
- 11
- LufteinlassbereichAir intake area
- 22
- TriebwerksgehäuseEngine casing
- 33
- eintretender Luftstromincoming airflow
- 44
- Kernstromnuclear power
- 55
- Nebenstromsidestream
- 66
- Fanfan
- 77
- KernstromkanalCore flow duct
- 88th
- NebenstromkanalBypass duct
- 99
- Leitschaufelkranzvane ring
- 1010
- Leitschaufelvane
- 10'10 '
- lange Leitschaufellong vane
- 1111
- Stützstrebesupport strut
- 1212
- Bifurkationbifurcation
- 1313
- Trennwandpartition wall
- 1414
- Druckseitepressure side
- 1515
- verlustminimalste Strömungloss-minimal flow
- 1616
- Saugseitesuction
- 1717
- verlustgrößte Strömungloss-largest flow
- 1818
-
Hinterkante von
10 Trailing edge of10 - 1919
-
Vorderkante von
11 Leading edge of11
Claims (3)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200910042242 DE102009042242A1 (en) | 2009-09-22 | 2009-09-22 | Turbofan driving gear has core duct and bypass duct and guide vane collar that is arranged in bypass duct, where selective positioning of supporting struts or bifurcations is determined in certain relation to guide vanes |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200910042242 DE102009042242A1 (en) | 2009-09-22 | 2009-09-22 | Turbofan driving gear has core duct and bypass duct and guide vane collar that is arranged in bypass duct, where selective positioning of supporting struts or bifurcations is determined in certain relation to guide vanes |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102009042242A1 true DE102009042242A1 (en) | 2011-04-14 |
Family
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DE200910042242 Ceased DE102009042242A1 (en) | 2009-09-22 | 2009-09-22 | Turbofan driving gear has core duct and bypass duct and guide vane collar that is arranged in bypass duct, where selective positioning of supporting struts or bifurcations is determined in certain relation to guide vanes |
Country Status (1)
Country | Link |
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DE (1) | DE102009042242A1 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3020951A1 (en) * | 2014-11-11 | 2016-05-18 | Rolls-Royce plc | Gas turbine engine duct with profiled region |
EP3020952A1 (en) * | 2014-11-11 | 2016-05-18 | Rolls-Royce plc | Gas turbine engine duct with profiled region |
GB2544553A (en) * | 2015-11-23 | 2017-05-24 | Rolls Royce Plc | Gas Turbine Engine |
EP2522809A3 (en) * | 2011-05-13 | 2018-04-04 | Rolls-Royce plc | A method of reducing asymmetric fluid flow effects in a passage |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2438696A (en) * | 2006-04-20 | 2007-12-05 | Rolls Royce Plc | Exhaust outlet for a turbine engine heat exchanger |
DE102006051375A1 (en) * | 2006-10-27 | 2008-04-30 | Rolls-Royce Deutschland Ltd & Co Kg | Aerodynamic covering for installations in engine mountings and supply lines, has compressed air stream blown into outer air stream in separation area with high energy and oscillates or pulsates depending on streaming behaviors |
-
2009
- 2009-09-22 DE DE200910042242 patent/DE102009042242A1/en not_active Ceased
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2438696A (en) * | 2006-04-20 | 2007-12-05 | Rolls Royce Plc | Exhaust outlet for a turbine engine heat exchanger |
DE102006051375A1 (en) * | 2006-10-27 | 2008-04-30 | Rolls-Royce Deutschland Ltd & Co Kg | Aerodynamic covering for installations in engine mountings and supply lines, has compressed air stream blown into outer air stream in separation area with high energy and oscillates or pulsates depending on streaming behaviors |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2522809A3 (en) * | 2011-05-13 | 2018-04-04 | Rolls-Royce plc | A method of reducing asymmetric fluid flow effects in a passage |
EP3020951A1 (en) * | 2014-11-11 | 2016-05-18 | Rolls-Royce plc | Gas turbine engine duct with profiled region |
EP3020952A1 (en) * | 2014-11-11 | 2016-05-18 | Rolls-Royce plc | Gas turbine engine duct with profiled region |
US10053997B2 (en) | 2014-11-11 | 2018-08-21 | Rolls-Royce Plc | Gas turbine engine |
US10215042B2 (en) | 2014-11-11 | 2019-02-26 | Rolls-Royce Plc | Gas turbine engine |
GB2544553A (en) * | 2015-11-23 | 2017-05-24 | Rolls Royce Plc | Gas Turbine Engine |
US10451005B2 (en) | 2015-11-23 | 2019-10-22 | Rolls-Royce Plc | Gas turbine engine |
GB2544553B (en) * | 2015-11-23 | 2020-02-19 | Rolls Royce Plc | Gas Turbine Engine |
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Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, DE Free format text: FORMER OWNER: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, 15827 BLANKENFELDE, DE Effective date: 20130402 |
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