DE102012003902A1 - Inlet for gas turbine, has inlet wall, bypass-channel formed at inner side of inlet wall, and bypass flow-stator arranged at end of bypass-channel, where inner side of bypass-channel is limited by bypass-channel wall that has drain holes - Google Patents
Inlet for gas turbine, has inlet wall, bypass-channel formed at inner side of inlet wall, and bypass flow-stator arranged at end of bypass-channel, where inner side of bypass-channel is limited by bypass-channel wall that has drain holes Download PDFInfo
- Publication number
- DE102012003902A1 DE102012003902A1 DE201210003902 DE102012003902A DE102012003902A1 DE 102012003902 A1 DE102012003902 A1 DE 102012003902A1 DE 201210003902 DE201210003902 DE 201210003902 DE 102012003902 A DE102012003902 A DE 102012003902A DE 102012003902 A1 DE102012003902 A1 DE 102012003902A1
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- DE
- Germany
- Prior art keywords
- bypass
- channel
- inlet
- wall
- gas turbine
- 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
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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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
- 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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- 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 einen Einlauf für eine Gasturbine. Sie betrifft ferner einen Kanal in einer Gasturbine. Die Erfindung betrifft schließlich eine Gasturbine mit einem derartigen Einlauf und/oder einem derartigen Kanal.The invention relates to an inlet for a gas turbine. It further relates to a channel in a gas turbine. Finally, the invention relates to a gas turbine with such an inlet and / or such a channel.
Gasturbinen umfassen üblicherweise einen Einlauf, einen Verdichter, eine Brennkammer, eine Turbine, eine Düse und eine oder mehrere Wellen. Der Einlauf weist in Strömungsrichtung einen ansteigenden Querschnitt auf. Der damit verbundene Gradient der Querschnittsvergrößerung in Strömungsrichtung kann zu einem Strömungsabriß im Bereich des Einlaufs führen.Gas turbines typically include an inlet, a compressor, a combustor, a turbine, a nozzle, and one or more shafts. The inlet has an ascending cross section in the flow direction. The associated gradient of the cross-sectional enlargement in the flow direction can lead to a stall in the region of the inlet.
In der Gasturbine können Kanäle vorgesehen sein. Insbesondere kann zwischen einem Niederdruckkompressor und einem Hochdruckkompressor ein Kanal vorgesehen sein. Bei diesem Kanal kann es sich insbesondere um einen Ringkanal handeln. Wenn der Kanal einen sich in Strömungsrichtung erweiternden Querschnitt aufweist, besteht die Gefahr eines Strömungsabrisses.Channels may be provided in the gas turbine. In particular, a channel may be provided between a low pressure compressor and a high pressure compressor. This channel may in particular be a ring channel. If the channel has a cross-sectional widening in the flow direction, there is a risk of a stall.
In beiden Fällen kann es durch die Gefahr des Strömungsabrisses erforderlich werden, den Gradienten der Querschnittsvergrößerung in Strömungsrichtung zu vermindern. Dies kann allerdings zu einer Verlängerung des Einlaufs und/oder des Kanals führen, was die Baulänge der gesamten Gasturbine in nachteiliger Weise vergrößern kann. Stattdessen oder zusätzlich kann der Druckunterschied im Einlauf und/oder in dem Kanal reduziert werden. Dies kann allerdings zu einer Verminderung des Wirkungsgrades führen.In both cases, the risk of stall may necessitate reducing the gradient of the cross-sectional enlargement in the flow direction. However, this can lead to an extension of the inlet and / or the channel, which can increase the overall length of the entire gas turbine disadvantageously. Instead or in addition, the pressure difference in the inlet and / or in the channel can be reduced. However, this can lead to a reduction in the efficiency.
Aufgabe der Erfindung ist es, einen verbesserten Einlauf für eine Gasturbine und/oder einen verbesserten Kanal in einer Gasturbine vorzuschlagen.The object of the invention is to propose an improved inlet for a gas turbine and / or an improved duct in a gas turbine.
Erfindungsgemäß wird diese Aufgabe bei einem Einlauf für eine Gasturbine durch die Merkmale des Anspruchs 1 gelöst. Der Einlauf umfaßt eine Einlaufwand. An der Innenseite der Einlaufwand ist ein Nebenstrom-Kanal vorgesehen, der an seiner Innenseite von einer Nebenstrom-Kanalwand begrenzt ist. Die Nebenstrom-Kanalwand weist eine Vielzahl von Abflußlöchern auf.This object is achieved in an inlet for a gas turbine by the features of
Vorteilhaft ist es, wenn am Ende des Nebenstrom-Kanals ein Nebenstrom-Stator angeordnet ist.It is advantageous if a bypass current stator is arranged at the end of the bypass duct.
Die der Erfindung zugrundeliegende Aufgabe wird bei einem Kanal in einer Gasturbine, insbesondere bei einem Ringkanal in einer Gasturbine, insbesondere bei einem Kanal oder Ringkanal von einem Niederdruckkompressor zu einem Hochdruckkompressor durch die Merkmale des Anspruchs 3 gelöst. Der Kanal umfaßt eine Außenwand. An der Innenseite der Außenwand ist ein Nebenstrom-Kanal vorgesehen, der an seiner Innenseite von einer Nebenstrom-Kanalwand begrenzt ist. Die Nebenstrom-Kanalwand weist eine Vielzahl von Abflußlöchern auf.The object underlying the invention is achieved in a channel in a gas turbine, in particular in an annular channel in a gas turbine, in particular in a channel or annular channel of a low-pressure compressor to a high pressure compressor by the features of
Vorteilhaft ist es, wenn am Ende des Nebenstrom-Kanals ein Nebenstrom-Stator angeordnet ist.It is advantageous if a bypass current stator is arranged at the end of the bypass duct.
Eine erfindungsgemäße Gasturbine ist gekennzeichnet durch einen erfindungsgemäßen Einlauf und/oder einen erfindungsgemäßen Kanal.A gas turbine according to the invention is characterized by an inlet according to the invention and / or a channel according to the invention.
Durch die Abflußlöcher in der Nebenstrom-Kanalwand wird Luft in den Nebenstrom-Kanal geleitet. Hierdurch kann eine Grenzschicht abgesaugt werden, so daß keine Grenzschichtablösung stattfinden kann. Auf diese Weise kann ein Strömungsabriß vermieden werden.Through the drain holes in the bypass duct wall, air is directed into the bypass duct. As a result, a boundary layer can be sucked off, so that no boundary layer separation can take place. In this way, a stall can be avoided.
Ausführungsbeispiele der Erfindung werden nachstehend anhand der beigefügten Zeichnung im einzelnen erläutert. In der Zeichnung zeigtEmbodiments of the invention are explained below with reference to the accompanying drawings in detail. In the drawing shows
Die in
Der Kompressor
Die Gasturbine umfaßt ferner einen Fan (Schaufelblatt-Rad)
Der Einlauf
Der Fan
In dem Kernstrom der Turbine ist ein Kanal
Der Kanal
In Strömungsrichtung hinter dem Nebenstrom-Kanal
Durch die Erfindung wird eine Gasturbine geschaffen, in deren Einlauf und/oder Kanal eine Grenzschichtablösung vermieden werden kann. Die Erfindung ermöglicht es, größere Gradienten der Querschnittserweiterung des Einlaufs und/oder des Kanals vorzusehen. Ferner kann der Wirkungsgrad erhöht werden. Die Abflußlöcher können in einem regelmäßigen oder unregelmäßigen Muster angeordnet sein. Durch einen Fan und/oder eine Verdichterschaufel in Strömungsrichtung hinter dem Nebenstrom-Kanal kann eine Saugwirkung in dem Nebenstrom-Kanal erzeugt werden.By the invention, a gas turbine is provided in the inlet and / or channel boundary layer separation can be avoided. The invention makes it possible to provide larger gradients of the cross-sectional widening of the inlet and / or the channel. Furthermore, the efficiency can be increased. The drainage holes may be arranged in a regular or irregular pattern. Through a fan and / or a compressor blade in the flow direction behind the bypass channel, a suction effect in the bypass channel can be generated.
Claims (5)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE201210003902 DE102012003902A1 (en) | 2011-12-14 | 2012-02-27 | Inlet for gas turbine, has inlet wall, bypass-channel formed at inner side of inlet wall, and bypass flow-stator arranged at end of bypass-channel, where inner side of bypass-channel is limited by bypass-channel wall that has drain holes |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102011121059.1 | 2011-12-14 | ||
DE102011121059 | 2011-12-14 | ||
DE201210003902 DE102012003902A1 (en) | 2011-12-14 | 2012-02-27 | Inlet for gas turbine, has inlet wall, bypass-channel formed at inner side of inlet wall, and bypass flow-stator arranged at end of bypass-channel, where inner side of bypass-channel is limited by bypass-channel wall that has drain holes |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102012003902A1 true DE102012003902A1 (en) | 2013-06-20 |
Family
ID=48522133
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE201210003902 Ceased DE102012003902A1 (en) | 2011-12-14 | 2012-02-27 | Inlet for gas turbine, has inlet wall, bypass-channel formed at inner side of inlet wall, and bypass flow-stator arranged at end of bypass-channel, where inner side of bypass-channel is limited by bypass-channel wall that has drain holes |
Country Status (1)
Country | Link |
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DE (1) | DE102012003902A1 (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3026240A1 (en) * | 2014-09-23 | 2016-06-01 | Pratt & Whitney Canada Corp. | Gas turbine engine with partial inlet vane |
US9938848B2 (en) | 2015-04-23 | 2018-04-10 | Pratt & Whitney Canada Corp. | Rotor assembly with wear member |
US9957807B2 (en) | 2015-04-23 | 2018-05-01 | Pratt & Whitney Canada Corp. | Rotor assembly with scoop |
US10145301B2 (en) | 2014-09-23 | 2018-12-04 | Pratt & Whitney Canada Corp. | Gas turbine engine inlet |
FR3074847A1 (en) * | 2017-12-13 | 2019-06-14 | Safran Aircraft Engines | BLOWER MODULE |
US10690146B2 (en) | 2017-01-05 | 2020-06-23 | Pratt & Whitney Canada Corp. | Turbofan nacelle assembly with flow disruptor |
US10724540B2 (en) | 2016-12-06 | 2020-07-28 | Pratt & Whitney Canada Corp. | Stator for a gas turbine engine fan |
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GB2149016A (en) * | 1983-10-31 | 1985-06-05 | Gen Electric | Air control system |
US5743488A (en) * | 1994-12-05 | 1998-04-28 | Short Brothers Plc | Aerodynamic low drag structure |
DE69524551T2 (en) * | 1994-11-28 | 2002-08-29 | Gen Electric | Blower for a turbo jet engine |
US20030035719A1 (en) * | 2001-08-17 | 2003-02-20 | Wadia Aspi Rustom | Booster compressor deicer |
US6698691B2 (en) * | 2001-02-15 | 2004-03-02 | Airbus France | Process for de-icing by forced circulation of a fluid, an air intake cowling of a reaction motor and device for practicing the same |
US20050060982A1 (en) * | 2003-09-22 | 2005-03-24 | General Electric Company | Method and system for reduction of jet engine noise |
US7144221B2 (en) * | 2004-07-30 | 2006-12-05 | General Electric Company | Method and apparatus for assembling gas turbine engines |
DE102006040757A1 (en) * | 2006-08-31 | 2008-04-30 | Rolls-Royce Deutschland Ltd & Co Kg | Fluid recirculation in the separator of fluid flow machines with bypass configuration |
US20110167784A1 (en) * | 2009-09-25 | 2011-07-14 | James Edward Johnson | Method of operating a convertible fan engine |
US8011172B2 (en) * | 2006-10-21 | 2011-09-06 | Rolls-Royce Plc | Engine arrangement |
-
2012
- 2012-02-27 DE DE201210003902 patent/DE102012003902A1/en not_active Ceased
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2149016A (en) * | 1983-10-31 | 1985-06-05 | Gen Electric | Air control system |
DE69524551T2 (en) * | 1994-11-28 | 2002-08-29 | Gen Electric | Blower for a turbo jet engine |
US5743488A (en) * | 1994-12-05 | 1998-04-28 | Short Brothers Plc | Aerodynamic low drag structure |
US6698691B2 (en) * | 2001-02-15 | 2004-03-02 | Airbus France | Process for de-icing by forced circulation of a fluid, an air intake cowling of a reaction motor and device for practicing the same |
US20030035719A1 (en) * | 2001-08-17 | 2003-02-20 | Wadia Aspi Rustom | Booster compressor deicer |
US20050060982A1 (en) * | 2003-09-22 | 2005-03-24 | General Electric Company | Method and system for reduction of jet engine noise |
US7144221B2 (en) * | 2004-07-30 | 2006-12-05 | General Electric Company | Method and apparatus for assembling gas turbine engines |
DE102006040757A1 (en) * | 2006-08-31 | 2008-04-30 | Rolls-Royce Deutschland Ltd & Co Kg | Fluid recirculation in the separator of fluid flow machines with bypass configuration |
US8011172B2 (en) * | 2006-10-21 | 2011-09-06 | Rolls-Royce Plc | Engine arrangement |
US20110167784A1 (en) * | 2009-09-25 | 2011-07-14 | James Edward Johnson | Method of operating a convertible fan engine |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3026240A1 (en) * | 2014-09-23 | 2016-06-01 | Pratt & Whitney Canada Corp. | Gas turbine engine with partial inlet vane |
EP3026240B1 (en) | 2014-09-23 | 2017-11-01 | Pratt & Whitney Canada Corp. | Gas turbine engine with partial inlet vane |
US10145301B2 (en) | 2014-09-23 | 2018-12-04 | Pratt & Whitney Canada Corp. | Gas turbine engine inlet |
US10378554B2 (en) | 2014-09-23 | 2019-08-13 | Pratt & Whitney Canada Corp. | Gas turbine engine with partial inlet vane |
US10837361B2 (en) | 2014-09-23 | 2020-11-17 | Pratt & Whitney Canada Corp. | Gas turbine engine inlet |
US11118601B2 (en) | 2014-09-23 | 2021-09-14 | Pratt & Whitney Canada Corp. | Gas turbine engine with partial inlet vane |
US9938848B2 (en) | 2015-04-23 | 2018-04-10 | Pratt & Whitney Canada Corp. | Rotor assembly with wear member |
US9957807B2 (en) | 2015-04-23 | 2018-05-01 | Pratt & Whitney Canada Corp. | Rotor assembly with scoop |
US10724540B2 (en) | 2016-12-06 | 2020-07-28 | Pratt & Whitney Canada Corp. | Stator for a gas turbine engine fan |
US10690146B2 (en) | 2017-01-05 | 2020-06-23 | Pratt & Whitney Canada Corp. | Turbofan nacelle assembly with flow disruptor |
FR3074847A1 (en) * | 2017-12-13 | 2019-06-14 | Safran Aircraft Engines | BLOWER MODULE |
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R012 | Request for examination validly filed | ||
R016 | Response to examination communication | ||
R016 | Response to examination communication | ||
R002 | Refusal decision in examination/registration proceedings | ||
R003 | Refusal decision now final |
Effective date: 20140423 |