EP1219781A2 - Vorrichtung und Verfahren zur Kühlung einer Plattform einer Turbinenschaufel - Google Patents
Vorrichtung und Verfahren zur Kühlung einer Plattform einer Turbinenschaufel Download PDFInfo
- Publication number
- EP1219781A2 EP1219781A2 EP01128807A EP01128807A EP1219781A2 EP 1219781 A2 EP1219781 A2 EP 1219781A2 EP 01128807 A EP01128807 A EP 01128807A EP 01128807 A EP01128807 A EP 01128807A EP 1219781 A2 EP1219781 A2 EP 1219781A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- platform
- cooling
- blade
- outlet
- turbine blade
- 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.)
- Granted
Links
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/80—Platforms for stationary or moving blades
- F05B2240/801—Platforms for stationary or moving blades cooled platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
Definitions
- the invention relates to a device and a method for cooling A platform of a turbine blade, which has a blade root, an airfoil a leading and trailing edge and a blade tip with a platform and which is at least partially penetrated radially by at least one cooling channel, the one with at least one emerging from the platform via an outlet opening Exit channel is connected.
- Cooling problems of the type mentioned above occur in particular Turbine blades that are used in gas turbine plants.
- the turbine blades are separated from the inside flows around the combustion chamber generated hot gases.
- Avoiding existing turbine blades plays the aspect of targeted cooling of gas turbine blades in the conception and design of such systems a major role.
- part of the cooling within the Compressor stage specifically derived and thus compressed air for cooling purposes withdrawn from the further combustion process. Rather, the cooling air passes over Cooling channel systems, both in rotating and stationary Plant components are provided in the area of the turbine stages around the there to cool the system components directly exposed to the hot gases.
- Cooling of the rotor assembly in a variety of axially one behind the other arranged rows of moving blades, have the Blades radial cooling channels through which from the side of the rotor assembly Cooling air fed in is guided longitudinally to the turbine blades, which are passed through cooling air openings correspondingly provided on the blade surface emerge and mixes with the hot gases.
- turbine blades point radially to the rotor assembly facing side platforms or so-called shrouds to Leakage flows between the turbine blade tips and the to train fixed system components.
- platforms and shrouds contribute to vibrations that occur train along the turbine blades during operation of the gas turbine, dampen effectively.
- a cooling duct system is used in US 5,482,435 for cooling such platforms described within a platform through which cooling air is conducted and thus effectively contributes to cooling the platform.
- the cooling air passes through a central cooling channel oriented radially to the turbine blade in the area of the platform, in which the cooling air escapes through two sub-channels.
- the one in the platform The partial cooling ducts provided extend in such a way that those from the platform emerging cooling air almost perpendicular to the main flow direction of the Gas turbine flowing hot gases is oriented. However, on the one hand, this causes that the flow behavior of the main flow is considerably irritated, causing the aerodynamic efficiency is permanently impaired.
- the cooling air emerging from the platform makes no contribution to the energy gain or contribute to improved energy conversion within the gas turbine.
- the invention has for its object a device and a method for Cooling a platform of a turbine blade according to the preamble of Claim 1 to develop such that, on the one hand, effective cooling of the Platform is ensured, but on the other hand it is ensured that the Main flow, which lies directly on the turbine blade, as little as possible is affected to the aerodynamic conditions within the Fluid machine not to deteriorate. Rather, it should be achieved that in addition to the above effective cooling effect, an additional energy gain can be achieved by the exit of the cooling air from the platform.
- a device for cooling a platform is a Turbine blade, which has a blade root, a blade with an attachment and Trailing edge, as well as a blade tip with a platform and the radial is at least partially penetrated by at least one cooling channel, which with at least one exiting the platform via an outlet opening Outlet channel is connected, further developed in that the outlet channel has a longitudinal channel direction adjacent to the outlet opening, which is in projection along the turbine blade largely coparallel to the direction of flow of a Exit flow immediately overflowing local flow field of a relative mass flow flowing past the turbine blade.
- the cooling device according to the invention is on all turbine blades applicable, which are provided with a platform.
- the with the invention The advantages associated with the measure are shown below using the example of Turbine guide vane explained in more detail within a gas turbine system. Of course, however, it is possible to use the cooling device according to the invention also to be used on platforms of stationary guide vanes.
- the Measure according to the invention is not based on the use of turbine blades limited within gas turbine stages of gas turbine plants, but can be used in all turbomachines in which corresponding Cooling problems occur, for example within compressors or the like Turbomachinery.
- the inventive arrangement of the outlet channel within the platform, by the cooling air exits through an outlet opening is oriented according to the invention in such a way so the cooling air that flows out of the platform is preferably the same Has flow direction with which the main flow of hot gases Turbine blade and thus also flows around the platform itself.
- the Outlet opening of the outlet channel on the turbine blade radially provided facing away from the top of the platform preferably runs the Cooling duct inclined slightly to the top of the platform.
- the Outlet opening attached to the downstream edge of the platform be so that the cooling air flowing out of the platform is coparallel to the die Hot gases flowing around the platform is oriented.
- there is Outlet opening of the cooling channel on the platform preferably downstream Leading edge of the turbine blade so that it is guaranteed that one is possible long cooling channel section runs within the platform, so that one if possible effective cooling effect can be achieved.
- Cooling arrangements within the platform which in the case of Turbine blades due to their radial spacing from the axis of rotation subjected to high centrifugal forces make an important contribution to the creep behavior of the blade material in the area of the platform increases positively influence, i.e. Material warping or deformation by softening the Materials under the influence of high centrifugal forces are effective cooling measures reduced or eliminated.
- Through the Cooling measure according to the invention within the platform can creep material be significantly restricted.
- the main advantage associated with this is the additional energy gain that comes with the targeted coparallel flow exit of the cooling air relative to the turbine blade mainstream flowing around, can be achieved. So it could be proven be that the cooling air coming from the cooling duct oriented according to the invention flows out through the outlet opening on the platform to a measurable Contributes to energy gain, which is characterized by the interaction of an additional Impulse contribution to the drive of the turbine blade and one comparatively negligible irritation or disturbance of the main flow of the Turbine blade flows around hot gases.
- a plurality of appropriately oriented cooling channels are preferred introduced within a platform, whereby the above described beneficial effects in terms of cooling effect and additional energy contribution let increase. Further details regarding possible exemplary embodiments can be found can be found in detail in the following exemplary embodiments.
- A are suitable for producing the platform designed according to the invention
- a variety of known techniques around the cooling channel or a variety bring appropriately oriented cooling channels into the platform.
- EDM processes Electro-Discharge Machining
- laser beam laser beam
- electrochemical Processes electrochemical Processes
- water jet techniques water jet techniques
- Figure 1 is a plan view of an axial arrangement consisting of a Guide vane row 1 and one downstream in the flow direction Blade row 2 shown.
- the platforms 3 are one Guide vane 4 and a moving blade 5 can be seen, the guide vane 4 or blade 5 facing away from the viewer perpendicular to the plane of the drawing extends.
- the main flow 6 through the turbine blades from the pure Redirected axial direction. So is the main flow 6 immediately after flowing through the guide vane row 1 directed upward in the circumferential direction, whereas the Main flow after flow around the blade row 2 against the direction of rotation is distracted.
- the inclination of the flow direction in relation to the axial direction becomes immediately downstream of a turbine blade row essentially due to the inclination the turbine blades relative to the main flow and the Circumferential speed conditional.
- the platforms 3 there are cooling channels 7, preferably in the region of the downstream end edge 8 of the platforms 3 arranged such that cooling air parallel to the main flow 6 from the Cooling channels 7 escapes.
- the longitudinal axes of the cooling channels 7 are parallel to Turbine airfoil in the area immediately upstream of the trailing edge 9 arranged.
- FIG 2 is the upper part of a longitudinal section through a turbine blade shown, which is designed for example as a rotor blade 5 and in its upper Area provides a platform 3.
- the rotor blade 5 has a radial direction extending main cooling duct 10, in the cooling air on the part of the shown blade root in the area of the platform 3.
- the main cooling channel 10 opens on one side a plurality of cooling channels 11, which are inclined run to the platform top 12 and there is an outlet opening 13 there provide. Cooling air through the outlet channels 11 through the respective Exit opening 13 on the platform top 3 exits is slightly oblique to Platform top 12, however, directed in the flow direction of the main flow 6.
- Further cooling channels 14 open out via corresponding further outlet openings the platform top and are appropriately provided through additional Cooling air channels 15 supplied with cooling air.
- the platform 3 of the moving blade 5 shown in FIG. 2 typically sees one trained labyrinth seal 16 before, directly below the cooling channel volume 17 with corresponding downstream outlet 18 is provided.
- FIG. 3 shows a top view of a platform 3, under which, in Extending in the longitudinal direction, a moving blade 5 is provided.
- the blade 5 has various hollow channels extending along the turbine blade, from which flows out of the hollow duct 10 cooling air in the direction of the platform.
- Immediately at the hollow channel 10 formed as a cooling channel includes Cooling air system through which the individual cooling channels 13 and 14 with appropriate cooling air is supplied. The cooling air flows along the individual Channels indicated arrow directions and occurs at the corresponding Exit openings 13, 14 on the top 12 of the platform 3.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- Fig. 1
- Draufsicht auf die axiale Anordnung einer in einer Laufschaufelreihe angeordnete Turbinenlaufschaufel sowie einer entsprechend axial stromauf angeordneten Turbinenleitschaufel,
- Fig. 2
- Teildarstellung durch einen radialen Längsschnitt durch eine Turbinenschaufel mit Plattform sowie
- Fig. 3
- Draufsicht auf eine Plattform in radialer Richtung.
- 1
- Leitschaufelreihe
- 2
- Laufschaufelreihe
- 3
- Plattform
- 4
- Leitschaufel
- 5
- Laufschaufel
- 6
- Hauptströmung
- 7
- Kühlkanäle
- 8
- stromabgewandtes Ende der Plattform 3
- 9
- Abströmkante
- 10
- Hauptkühlkanal
- 11
- Kühlkanal
- 12
- Plattformoberseite
- 13
- Austrittsöffnung
- 14
- Austrittsöffnung
- 15
- Nebenkühlkanal
- 16
- Labyrinthdichtung
- 17
- Kühlkanalvolumen
- 18
- Auslasskanal
Claims (8)
- Vorrichtung zur Kühlung einer Plattform (3) einer Turbinenschaufel, die einen Schaufelfuß, ein Schaufelblatt mit einer An- und Abströmkante, sowie eine Schaufelspitze mit einer Plattform (3) vorsieht und die radial von wenigstens einem Kühlkanal wenigstens teilweise durchsetzt ist, der mit wenigstens einem, über eine Austrittsöffnung an der Plattform austretenden Austrittskanal verbunden ist,
dadurch gekennzeichnet, dass der Austrittskanal (7,11) angrenzend zur Austrittsöffnung (13) eine Kanallängsrichtung aufweist, die in Projektion längs zur Turbinenschaufel weitgehend koparallel zur Strömungsrichtung eines die Austrittsöffnung unmittelbar überströmenden, lokalen Strömungsfeldes (6) eines relativ an der Turbinenschaufel vorbeiströmenden Massenflusses verläuft. - Vorrichtung nach Anspruch 1,
dadurch gekennzeichnet, dass der Austrittskanal (7,11) angrenzend zur Austrittsöffnung (13) eine Kanallängsrichtung aufweist, die in Projektion längs zur Turbinenschaufel weitgehend koparallel zum Axialschnitt des Turbinenschaufelblattes im Bereich unmittelbar stromauf zur Abströmkante verläuft. - Vorrichtung nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass durch den Austrittskanal (7,11) ein Kühlmedium, vorzugweise Kühlluft, strömbar ist, das die Austrittsöffnung (13) nahezu in Strömungsrichtung zum lokalen Strömungsfeld (6) verläßt. - Vorrichtung nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass die Turbinenschaufel in einer Strömungsmaschine, vorzugsweise in einer Gasturbine, integriert ist, durch die der Massenfluss axial hindurchgerichtet ist. - Vorrichtung nach einem der Ansprüche 1 bis 4,
dadurch gekennzeichnet, dass die Austrittsöffnung (13) nahe dem stromabgewandten Ende der Plattform (3) angeordnet ist. - Vorrichtung nach einem der Ansprüche 1 bis 5,
dadurch gekennzeichnet, dass die Plattform (3) eine dem Turbinenschaufelblatt radial abgewandte Plattformoberseite (12) aufweist, an der die Austrittsöffnung (13) vorgesehen ist. - Vorrichtung nach einem der Ansprüche 1 bis 6,
dadurch gekennzeichnet, dass die Turbinenschaufel eine Leit- vorzugsweise eine Laufschaufel innerhalb einer Gasturbine ist. - Verfahren zur Kühlung einer Plattform einer Turbinenschaufel, die einen Schaufelfuß, ein Schaufelblatt mit einer An- und Abströmkante, sowie eine Schaufelspitze mit einer Plattform vorsieht und die radial von wenigstens einem Kühlkanal wenigstens teilweise durchsetzt ist, der mit wenigstens einem, über eine Austrittsöffnung an der Plattform austretenden Austrittskanal verbunden ist,
dadurch gekennzeichnet, dass ein Kühlmedium, vorzugsweise Kühlluft durch den Kühlkanal und den Austrittskanal derart hindurchgeleitet wird und aus der Plattform austritt, dass das Kühlmedium nahezu strömungsparallel in Richtung zu einem die Turbinenschaufel umströmenden Massenstrom die Plattform verlässt.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10064265 | 2000-12-22 | ||
DE10064265A DE10064265A1 (de) | 2000-12-22 | 2000-12-22 | Vorrichtung und Verfahren zur Kühlung einer Plattform einer Turbinenschaufel |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1219781A2 true EP1219781A2 (de) | 2002-07-03 |
EP1219781A3 EP1219781A3 (de) | 2004-01-21 |
EP1219781B1 EP1219781B1 (de) | 2007-05-02 |
Family
ID=7668438
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01128807A Expired - Lifetime EP1219781B1 (de) | 2000-12-22 | 2001-12-04 | Vorrichtung und Verfahren zur Kühlung einer Plattform einer Turbinenschaufel |
Country Status (3)
Country | Link |
---|---|
US (1) | US6641360B2 (de) |
EP (1) | EP1219781B1 (de) |
DE (2) | DE10064265A1 (de) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1630354A2 (de) | 2004-08-25 | 2006-03-01 | Rolls-Royce Plc | Gekühlte Gasturbinenschaufel |
CN101482032A (zh) * | 2008-01-10 | 2009-07-15 | 通用电气公司 | 涡轮叶片叶冠 |
WO2012007250A1 (en) * | 2010-07-15 | 2012-01-19 | Siemens Aktiengesellschaft | Nozzle guide vane with cooled platform for a gas turbine |
EP2607629A1 (de) * | 2011-12-22 | 2013-06-26 | Alstom Technology Ltd | Turbinenschaufel mit Deckband und Kühlluftauslassöffnung an der Schaufelspitze und zugehöriges Herstellungsverfahren |
RU2575260C2 (ru) * | 2010-07-15 | 2016-02-20 | Сименс Акциенгезелльшафт | Сопловая лопатка с охлаждаемой платформой для газовой турбины |
EP3163025A1 (de) * | 2015-10-27 | 2017-05-03 | General Electric Company | Turbinenschaufel mit auslassöffnung in deckband |
Families Citing this family (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB0228443D0 (en) * | 2002-12-06 | 2003-01-08 | Rolls Royce Plc | Blade cooling |
US6945749B2 (en) * | 2003-09-12 | 2005-09-20 | Siemens Westinghouse Power Corporation | Turbine blade platform cooling system |
US7114339B2 (en) * | 2004-03-30 | 2006-10-03 | United Technologies Corporation | Cavity on-board injection for leakage flows |
EP1591626A1 (de) * | 2004-04-30 | 2005-11-02 | Alstom Technology Ltd | Schaufel für Gasturbine |
DE102004037331A1 (de) * | 2004-07-28 | 2006-03-23 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenrotor |
US7131817B2 (en) * | 2004-07-30 | 2006-11-07 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
US7198467B2 (en) * | 2004-07-30 | 2007-04-03 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
US7144215B2 (en) * | 2004-07-30 | 2006-12-05 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
WO2006029983A1 (de) * | 2004-09-16 | 2006-03-23 | Alstom Technology Ltd | Strömungsmaschinenschaufel mit fluidisch gekühltem deckband |
US7186089B2 (en) * | 2004-11-04 | 2007-03-06 | Siemens Power Generation, Inc. | Cooling system for a platform of a turbine blade |
US7708525B2 (en) * | 2005-02-17 | 2010-05-04 | United Technologies Corporation | Industrial gas turbine blade assembly |
US7309212B2 (en) * | 2005-11-21 | 2007-12-18 | General Electric Company | Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge |
US7416391B2 (en) * | 2006-02-24 | 2008-08-26 | General Electric Company | Bucket platform cooling circuit and method |
CN100513630C (zh) * | 2006-03-24 | 2009-07-15 | 统宝光电股份有限公司 | 蒸镀系统 |
US7686581B2 (en) * | 2006-06-07 | 2010-03-30 | General Electric Company | Serpentine cooling circuit and method for cooling tip shroud |
US7534088B1 (en) | 2006-06-19 | 2009-05-19 | United Technologies Corporation | Fluid injection system |
US7946816B2 (en) * | 2008-01-10 | 2011-05-24 | General Electric Company | Turbine blade tip shroud |
US8147197B2 (en) * | 2009-03-10 | 2012-04-03 | Honeywell International, Inc. | Turbine blade platform |
US8079814B1 (en) * | 2009-04-04 | 2011-12-20 | Florida Turbine Technologies, Inc. | Turbine blade with serpentine flow cooling |
US8356978B2 (en) * | 2009-11-23 | 2013-01-22 | United Technologies Corporation | Turbine airfoil platform cooling core |
US9630277B2 (en) * | 2010-03-15 | 2017-04-25 | Siemens Energy, Inc. | Airfoil having built-up surface with embedded cooling passage |
US8356975B2 (en) * | 2010-03-23 | 2013-01-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured vane platform |
US9976433B2 (en) | 2010-04-02 | 2018-05-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured rotor blade platform |
US8636470B2 (en) | 2010-10-13 | 2014-01-28 | Honeywell International Inc. | Turbine blades and turbine rotor assemblies |
JP5916294B2 (ja) * | 2011-04-18 | 2016-05-11 | 三菱重工業株式会社 | ガスタービン動翼及びその製造方法 |
WO2014130244A1 (en) | 2013-02-19 | 2014-08-28 | United Technologies Corporation | Gas turbine engine airfoil platform cooling passage and core |
US10001013B2 (en) | 2014-03-06 | 2018-06-19 | General Electric Company | Turbine rotor blades with platform cooling arrangements |
US10184342B2 (en) * | 2016-04-14 | 2019-01-22 | General Electric Company | System for cooling seal rails of tip shroud of turbine blade |
EP3351341A1 (de) * | 2017-01-23 | 2018-07-25 | Siemens Aktiengesellschaft | Verfahren zur herstellung eines hohlraums in einer schaufelplattform |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5482435A (en) | 1994-10-26 | 1996-01-09 | Westinghouse Electric Corporation | Gas turbine blade having a cooled shroud |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IT1079131B (it) * | 1975-06-30 | 1985-05-08 | Gen Electric | Perfezionato raffreddamento applicabile particolarmente a elementi di turbomotori a gas |
GB1514613A (en) * | 1976-04-08 | 1978-06-14 | Rolls Royce | Blade or vane for a gas turbine engine |
GB9224241D0 (en) | 1992-11-19 | 1993-01-06 | Bmw Rolls Royce Gmbh | A turbine blade arrangement |
US5382135A (en) * | 1992-11-24 | 1995-01-17 | United Technologies Corporation | Rotor blade with cooled integral platform |
US5387085A (en) * | 1994-01-07 | 1995-02-07 | General Electric Company | Turbine blade composite cooling circuit |
US5503529A (en) * | 1994-12-08 | 1996-04-02 | General Electric Company | Turbine blade having angled ejection slot |
GB2298245B (en) * | 1995-02-23 | 1998-10-28 | Bmw Rolls Royce Gmbh | A turbine-blade arrangement comprising a cooled shroud band |
US6092982A (en) * | 1996-05-28 | 2000-07-25 | Kabushiki Kaisha Toshiba | Cooling system for a main body used in a gas stream |
DE59710924D1 (de) * | 1997-09-15 | 2003-12-04 | Alstom Switzerland Ltd | Kühlvorrichtung für Gasturbinenkomponenten |
DE59810560D1 (de) * | 1998-11-30 | 2004-02-12 | Alstom Switzerland Ltd | Schaufelkühlung |
-
2000
- 2000-12-22 DE DE10064265A patent/DE10064265A1/de not_active Withdrawn
-
2001
- 2001-12-04 DE DE50112433T patent/DE50112433D1/de not_active Expired - Lifetime
- 2001-12-04 EP EP01128807A patent/EP1219781B1/de not_active Expired - Lifetime
- 2001-12-06 US US10/003,419 patent/US6641360B2/en not_active Expired - Lifetime
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5482435A (en) | 1994-10-26 | 1996-01-09 | Westinghouse Electric Corporation | Gas turbine blade having a cooled shroud |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1630354A2 (de) | 2004-08-25 | 2006-03-01 | Rolls-Royce Plc | Gekühlte Gasturbinenschaufel |
EP1630354A3 (de) * | 2004-08-25 | 2009-10-28 | Rolls-Royce Plc | Gekühlte Gasturbinenschaufel |
CN101482032A (zh) * | 2008-01-10 | 2009-07-15 | 通用电气公司 | 涡轮叶片叶冠 |
WO2012007250A1 (en) * | 2010-07-15 | 2012-01-19 | Siemens Aktiengesellschaft | Nozzle guide vane with cooled platform for a gas turbine |
RU2575260C2 (ru) * | 2010-07-15 | 2016-02-20 | Сименс Акциенгезелльшафт | Сопловая лопатка с охлаждаемой платформой для газовой турбины |
US9856747B2 (en) | 2010-07-15 | 2018-01-02 | Siemens Aktiengesellschaft | Nozzle guide vane with cooled platform for a gas turbine |
EP2607629A1 (de) * | 2011-12-22 | 2013-06-26 | Alstom Technology Ltd | Turbinenschaufel mit Deckband und Kühlluftauslassöffnung an der Schaufelspitze und zugehöriges Herstellungsverfahren |
EP3163025A1 (de) * | 2015-10-27 | 2017-05-03 | General Electric Company | Turbinenschaufel mit auslassöffnung in deckband |
CN106968718A (zh) * | 2015-10-27 | 2017-07-21 | 通用电气公司 | 具有护罩中的出口路径的涡轮轮叶 |
US10508554B2 (en) | 2015-10-27 | 2019-12-17 | General Electric Company | Turbine bucket having outlet path in shroud |
US11078797B2 (en) | 2015-10-27 | 2021-08-03 | General Electric Company | Turbine bucket having outlet path in shroud |
Also Published As
Publication number | Publication date |
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US6641360B2 (en) | 2003-11-04 |
US20020098078A1 (en) | 2002-07-25 |
DE10064265A1 (de) | 2002-07-04 |
EP1219781B1 (de) | 2007-05-02 |
DE50112433D1 (de) | 2007-06-14 |
EP1219781A3 (de) | 2004-01-21 |
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