EP1215363B1 - Gekühlte Gasturbinenschaufel - Google Patents
Gekühlte Gasturbinenschaufel Download PDFInfo
- Publication number
- EP1215363B1 EP1215363B1 EP01128573A EP01128573A EP1215363B1 EP 1215363 B1 EP1215363 B1 EP 1215363B1 EP 01128573 A EP01128573 A EP 01128573A EP 01128573 A EP01128573 A EP 01128573A EP 1215363 B1 EP1215363 B1 EP 1215363B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cover plate
- gas turbine
- turbine blade
- cooled gas
- shroud
- 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.)
- Expired - Lifetime
Links
Images
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—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
- F01D5/187—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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- 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
- 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
-
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/19—Two-dimensional machined; miscellaneous
- F05D2250/191—Two-dimensional machined; miscellaneous perforated
Definitions
- the invention relates to a cooled gas turbine blade with a Shroud in which a cooling channel system is provided, which is radially to Gas turbine blade is completed with a cover plate.
- the heat-exposed plant components can be increased by providing appropriate cooling duct systems through targeted supply of Cooling air actively cooled.
- Gas turbine blades are present in a manner known per se, regardless of whether they are to guide or moving blades, usually from a blade root and an airfoil, which is usually projected radially from a shroud.
- the im Inside a gas turbine blade provided cooling system is usually from a plurality of individual cooling channels extending radially from the sides of the blade root extend through the entire turbine blade to the shroud.
- Within the shroud cooling duct areas are provided in which the cooling air and Deflection flow guide structures are provided to the cooling effect within to improve the shroud.
- the cooling channels producing casting core present turbine blade especially in the area of the shroud large openings, although a subsequent insertion of the aforementioned flow guide structures,
- a baffle-cooling plate but allow, it is gas-tight seal.
- Closure plate or so-called cover plate usually with the shroud the gas turbine blade is connected by means of high temperature soldering.
- Fig. 2a to 2c is a known connection between a cover plate. 6 and the shroud 2 of a turbine blade.
- Fig. 2a is a perspective view of a turbine blade with an airfoil 1 and a shroud 2 shown.
- the shroud 2 has two each with a groove contour. 3 trained side edges 4 and 5, along which a cover plate. 6 is inserted positively.
- the cross section along the section line S1 is shown in FIG. 2b.
- the groove contour 3 partially covers the in the shroud. 2 inserted cover plate 5, in addition to the positive connection between the groove contour 3 and the cover plate 6 is fixed by a solder joint 7. From the Cross-sectional view according to FIG. 2b are those between the cover plate 6 and the cover band 2 enclosed cooling channels K to remove through the cooling air by not shown in the further cooling system within the Gas turbine blade is passed.
- the invention is based on the object, a cooled gas turbine blade with a shroud, in which a cooling channel system is provided, which is radially to the Gas turbine blade is completed with a cover plate to train such that the cover plate is provided with the shroud in a secure manner and at the above-mentioned total loss of the cover plate are excluded can. Furthermore, leakage losses occur when cracks occur in the joint connection between the cover plate and the shroud to minimize crucial. The too appropriate measures should thereby only a small design effort by which the manufacturing cost of cooled gas turbine blades not or only slightly more expensive.
- a cooled gas turbine blade according to the preamble of Claim 1 formed such that the cover plate has a peripheral edge, along the entire extent of the cover plate with the shroud of Gas turbine blade a continuous form joint or a variety locally Limited form compounds received.
- an inventively designed shroud looks at the shape and size of the peripheral edge of the cover plate adapted receiving contour in Meaning of a box frame, in which the cover plate radially to the full extent can be inserted.
- the receiving contour preferably has one stepped cross-section, comparable to that of a picture frame in which a Picture can be pasted on the back.
- the step-shaped cross-section of Receiving contour in this case has a radially or obliquely radially first and one axially oriented second step surface, the so-called contact surface, on the the cover plate can be placed with its entire peripheral edge.
- the Direction data radially or axially refer to conventional Directional information, in conjunction with an axial flowed rotor assembly usually used within a gas turbine plant.
- a joining agent preferably soldering material
- the solder material is selected such that the Solders after the soldering and / or heat treatment process no or only has a low ductility, so is brittle.
- solder material inherent brittleness occur at the beginning of the first commissioning of the gas turbine blades due to thermally induced Deformations cracks within the solder seam, which turn out to be "zigzag” shaped form extending fracture lines or surfaces and the soldering seam completely push through. Surprisingly, it is precisely these training Fracture surfaces that guarantee a secure fit and also to a BiegeHarsstage solder joint between cover plate and shroud contribute.
- the forming within the solder seam hair tear basically a Cooling air leakage is limited by the cooling air from that of the cover plate Cooling air system within the gas turbine blade can escape to the outside, but this cooling air loss is negligible and does not matter further.
- form on the surfaces of the crack within the solder seam Oxidation layers on the one hand able to reduce the crack gap and in addition, for a play-free fit of the cover plate within the through Lötnaht predetermined positive connection despite prevailing large Ensure vibrations during operation of the gas turbine.
- this provides the first, preferably radially oriented step surface of the receiving contour within the shroud a circumferential mounting groove in front, in the at least half the outer contour of a Snap ring can engage, which surrounds the cover plate in a suitable form.
- One Inserting the cover plate in the receiving contour of the shroud is done by mechanical constriction of the circlip following correspondingly have within the mounting groove in the shroud spread out and thus a positive connection between shroud and cover plate guaranteed.
- rod-shaped holding means to create a Positive connection between cover plate and shroud can be used by passing them through suitable holes in the cover plate and the Shroud to be inserted.
- the rod-like holding means can tangential or radial running between cover plate and shroud in corresponding mounting holes are inserted. While being on this Do not cover the top plate along its entire peripheral edge continuous positive connection with the shroud has, as it is in a circumferential solder joint is the case, but is also in this way for a secure fit of the cover plate provided in the shroud.
- Fig. 1a shows a perspective top view of a gas turbine blade with a Shroud 2, which at its radially oriented upper side a rectangular Recess 10 provides, in which the cover plate 6 radially from above completely is inserted. Between the cover plate 6 and the shroud 2 is a solder seam. 7 introduced, which completely surrounds the peripheral contour of the cover plate 6.
- Fig.1b is a cross section through an arbitrary position transverse to the receiving contour shown within the shroud 2.
- the receiving contour of the shroud 2 has a first obliquely radially directed first step surface 11 and one axially oriented second step surface, the so-called support surface 12.
- the step depth the receiving contour is preferably just chosen so that the surface of the Cover plate 6 is flush with the surface of the shroud 2.
- a Intermediate gap 13 is provided, which is at least chosen so large that a simple Inserting the cover plate 6 in the receiving contour of the shroud 2, due to a existing installation play 16 is possible.
- the between the cover plate 6 and the shroud 2 located intermediate gap 13 is subsequently with solder 14th completely filled and soldered, the solder 14 has the lowest possible Has ductility or high brittle hardness after the soldering process.
- FIG. 3a shows such a crack 15, which consists of two Zigzag-shaped, directly opposite fracture surfaces composed. Since the crack course takes a statistical course and thus along the fracture surfaces has fracture surface portions which are inclined to the Radial direction of the gas turbine blade and thus to the at the Gas turbine blade attacking centrifugal forces are inclined, wearing an intimate Gearing between the cover plate 6 and the shroud along the Lötnaht thereto in that the cover plate 6 can not come off the shroud 2. Furthermore allows the loose multi-pronged form-fitting connection a stress-free seat the cover plate 6 within the shroud, whereby the cover plate 6 lower mechanical stresses as well as vibrations is exposed.
- Fig. 3b shows a joining variant using an additional Closure strip 16, which is soldered on both sides by two solder seams 7, 7 '.
- the Closure strip 16 is made of a high temperature resistant material, which has a much higher ductility than the material itself, so that the Closure strip 16 to a vibration damping of the cover plate 6 within contributes the shroud 2.
- FIG. 4a the insertion process of the cover plate 6 is shown in the receiving contour of the shroud 2.
- An installation play 16 present between the cover strip 2 and the cover plate 6 ensures unimpeded radial insertion of the cover plate 6 into the cover strip 2.
- FIG. 4b shows the insertion of a closure piece 17 as a function of a mechanical holding means 18 , which is integrally formed as a molded part in the intermediate gap 13 is inserted.
- the closure piece 1 7 has a sufficiently high ductility and high temperature resistance, so that it is able to transfer the forces occurring between the cover plate 6 and the shroud 2 harmless.
- Fig. 4c a force distribution between the cover plate 6, the closure piece 17 and the shroud 2 is shown.
- Fig. 5a, b and c are different embodiments of Positive connection between the cover plate 6 and the shroud. 2 shown.
- Fig. 5a is a radially directed gap between shroud 2 and Cover plate 6 filled with solder material.
- Fig. 5b shows an obliquely radially inclined soldering gap.
- Fig. 5c the intermediate gap between the cover plate 6 and Shroud 2 radially formed and only in the upper region is a wedge-shaped solder joint 7 introduced. This surpasses this Shroud 2, the cover plate 6 a little, so that a dreieickförmiger solder wedge. 7 can form between shroud 2 and cover plate 6.
- a Set crack course which is approximately 45 ° relative to the radial direction and thus to a stable positive connection between the cover plate 6 and the Shroud 2 leads.
- Fig. 6 shows For this purpose, a corresponding connection cross section between cover plate 6 and Shroud 2. Between the shroud 2 and the cover plate 6 is a snap ring 18th introduced on both sides partially in the peripheral edge of the cover plate 6 and in the shroud 2 protrudes.
- a snap ring 18 rod-shaped molded body can be provided by lateral mounting openings within the cover strip and the cover plate can be introduced.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- Fig. 1a
- perspektivische Draufsicht auf ein Deckband mit eingesetzter Deckplatte,
- Fig. 1 b
- Querschnitt durch die Aufnahmekontur eines Deckbandes mit eingefügter Deckplatte,
- Fig. 2a,b,c
- Darstellungen einer bekannte Deckplatte-Deckband-Verbindung (Stand der Technik),
- Fig. 3a, b
- Darstellungen zur Rissbildung innerhalb der Lötnaht,
- Fig. 4a bis c
- Formschlussverbindung mittels Einsatzteil,
- Fig. 5 a,b,c
- Darstellung alternativer Fügegeometrien,
- Fig. 6
- Darstellung von Formschlussverbindungen mittels mechanischem Haltemittel.
- 1
- Schaufelblatt
- 2
- Deckband
- 3
- Nutkontur
- 4,5
- Seitenkanten des Deckbandes
- 6
- Deckplatte
- 7
- Lötmaterial
- 8,9
- Seitenkanten des Deckbandes
- 10
- Ausnehmung
- 11
- Erste Stufenfläche
- 12
- Zweite Stufenfläche
- 13
- Zwischenspalt
- 14
- Lömaterial
- 15
- Riss
- 16
- Einbauspiel
- 17
- Verschlusselement
- 18
- Mechanisches Haltemittel
- K
- Kühlkanäle
Claims (12)
- Gekühlte Gasturbinenschaufel mit einem Deckband (2), in dem ein Kühlkanalsystem (K) vorgesehen ist, das radial zur Gasturbinenschaufel mit einer Deckplatte (6) abgeschlossen ist,
dadurch gekennzeichnet, dass die Deckplatte (6) einen Umfangsrand aufweist, längs dessen gesamter Erstreckung die Deckplatte (6) mit dem Deckband (2) eine durchgehende Formverbindung oder eine Vielzahl lokal begrenzter Formverbindungen eingeht. - Gekühlte Gasturbinenschaufel nach Anspruch 1,
dadurch gekennzeichnet, dass die Vielzahl lokal begrenzter Formverbindungen gleichmäßig längs des Umfangsrandes verteilt sind. - Gekühlte Gasturbinenschaufel nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass das Deckband (2) eine nach Form und Größe des Umfangsrandes der Deckplatte (6) angepaßte Aufnahmekontur aufweist, mit einem stufenförmigen Querschnitt, der eine radial- oder schräg radialwärts erste (11) und eine axialwärts orientierte zweite Stufenfläche (12), die sogenannte Auflagefläche, vorsieht, auf der die Deckplatte (6) radialwärts aufsetzbar ist, und
dass im Bereich zwischen der ersten Stufenfläche (11) und dem Umfangsrand der Deckplatte (6) ein Haltemittel eingebracht ist, das die Formverbindung gewährleistet. - Gekühlte Gasturbinenschaufel nach Anspruch 3,
dadurch gekennzeichnet, dass zwischen der ersten Stufenfläche (11) und der in die Aufnahmekontur eingesetzten Deckplatte (6) ein Zwischenspalt (13) vorgesehen ist. - Gekühlte Gasturbinenschaufel nach Anspruch 4,
dadurch gekennzeichnet, dass die erste Stufenfläche (11) und der Umfangsrand geradlinig ausgebildet sind und der Zwischenspalt (13) eine weitgehend konstante Spaltbreite aufweist, und
dass der Zwischenspalt (13) radial oder schräg-radial zur Gasturbinenschaufellängsrichtung orientiert ist. - Gekühlte Gasturbinenschaufel nach einem der Ansprüche 3 bis 5,
dadurch gekennzeichnet, dass das Haltemittel ein Fügemittel ist, das im Bereich zwischen der ersten Stufenfläche (11) und dem Umfangsrand der Deckplatte (6) eingebracht ist und eine innige Fügeverbindung jeweils mit der ersten Stufenfläche (11) und dem Umfangsrand eingeht, und
dass innerhalb des Fügemittels längs der Erstreckung beider Fügeverbindungen wenigstens eine das Fügemittel vollständig durchsetzende Bruchfläche (15) vorgesehen ist mit schräg zur Radialrichtung verlaufenden Bruchflächenabschnitten. - Gekühlte Gasturbinenschaufel nach Anspruch 6,
dadurch gekennzeichnet, dass das Fügemittel ein Lötmaterial (7) ist, das über keine oder nur geringe Duktilität verfügt. - Gekühlte Gasturbinenschaufel nach einem der Ansprüche 3 bis 6,
dadurch gekennzeichnet, dass die erste Stufenfläche (11) derart bemessen ist, dass sie die in die Aufnahmekontur eingesetzte Deckplatte (6) überragt,
dass das Fügemittel zumindest oberhalb der Deckplatte (6) zwischen der Deckplatte (6) und der die Deckplatte (6) überragenden ersten Stufenfläche (11) vorgesehen ist, und dass die Bruchfläche (15) schräg radial das Fügemittel durchsetzt. - Gekühlte Gasturbinenschaufel nach Anspruch 8,
dadurch gekennzeichnet, dass die Bruchfläche (15) im Winkelbereich von etwa 45° bezogen auf die Deckplatte (6) verläuft. - Gekühlte Gasturbinenschaufel nach Anspruch 3,
dadurch gekennzeichnet, dass der Umfangsrand der Deckplatte (6) eine längs des Umfangsrandes verlaufende Befestigungskontur aufweist, in die ein mechanisches Haltemittel (18) einbringbar ist, und
dass längs der ersten Stufenfläche (11) eine zur Befestigungskontur der Deckplatte (6) korrespondierende Befestigungskontur vorgesehen ist, in die im verfügten Zustand der Deckplatte (6) innerhalb der Aufnahmekontur das mechanische Haltemittel (18) kraftschlüssig einmündet. - Gekühlte Gasturbinenschaufel nach Anspruch 10,
dadurch gekennzeichnet, dass das mechanische Haltemittel (18) eine Art Sprengring ist, der innerhalb der Befestigungskontur der Deckplatte (6) vorgesehen ist. - Gekühlte Gasturbinenschaufel nach Anspruch 10,
dadurch gekennzeichnet, dass das mechanische Haltemittel (18) aus einer Anzahl stangenförmig ausgebildeter Formkörper besteht, die durch seitliche Montageöffnungen innerhalb des Deckbandes zwischen Umfangsrand der Deckplatte und erster Stufenfläche in die Befestigungskontur einbringbar sind.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10062907 | 2000-12-16 | ||
DE10062907 | 2000-12-16 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1215363A2 EP1215363A2 (de) | 2002-06-19 |
EP1215363A3 EP1215363A3 (de) | 2004-01-02 |
EP1215363B1 true EP1215363B1 (de) | 2005-10-05 |
Family
ID=7667527
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01128573A Expired - Lifetime EP1215363B1 (de) | 2000-12-16 | 2001-11-30 | Gekühlte Gasturbinenschaufel |
EP01128572A Expired - Lifetime EP1215364B1 (de) | 2000-12-16 | 2001-11-30 | Vorrichtung zur Kühlung eines Deckbandes einer Gasturbinenschaufel |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01128572A Expired - Lifetime EP1215364B1 (de) | 2000-12-16 | 2001-11-30 | Vorrichtung zur Kühlung eines Deckbandes einer Gasturbinenschaufel |
Country Status (4)
Country | Link |
---|---|
US (2) | US6682304B2 (de) |
EP (2) | EP1215363B1 (de) |
JP (1) | JP2002201907A (de) |
DE (4) | DE10131073A1 (de) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2328111B1 (de) | 2002-05-09 | 2018-12-12 | Sony Corporation | Authentifizierung anhand von Blutgefäßen |
AU2005284134B2 (en) | 2004-09-16 | 2008-10-09 | General Electric Technology Gmbh | Turbine engine vane with fluid cooled shroud |
US20070048122A1 (en) * | 2005-08-30 | 2007-03-01 | United Technologies Corporation | Debris-filtering technique for gas turbine engine component air cooling system |
US20110110772A1 (en) * | 2009-11-11 | 2011-05-12 | Arrell Douglas J | Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same |
US9133724B2 (en) * | 2012-01-09 | 2015-09-15 | General Electric Company | Turbomachine component including a cover plate |
US9567857B2 (en) | 2013-03-08 | 2017-02-14 | Rolls-Royce North American Technologies, Inc. | Turbine split ring retention and anti-rotation method |
US10590785B2 (en) * | 2014-09-09 | 2020-03-17 | United Technologies Corporation | Beveled coverplate |
DE102017208680A1 (de) | 2017-05-23 | 2018-11-29 | Siemens Aktiengesellschaft | Verfahren zum Befestigen eines Kühlbleches an einer Turbinenschaufel |
US10370300B2 (en) * | 2017-10-31 | 2019-08-06 | General Electric Company | Additively manufactured turbine shroud segment |
US11156102B2 (en) * | 2018-03-19 | 2021-10-26 | General Electric Company | Blade having a tip cooling cavity and method of making same |
CN114405715B (zh) * | 2021-12-28 | 2023-08-18 | 东方电气集团东方汽轮机有限公司 | 一种燃气轮机空心叶片喷涂用装夹工装 |
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NL88170C (de) * | 1952-10-31 | 1900-01-01 | ||
US3756020A (en) * | 1972-06-26 | 1973-09-04 | Curtiss Wright Corp | Gas turbine engine and cooling system therefor |
US3781129A (en) * | 1972-09-15 | 1973-12-25 | Gen Motors Corp | Cooled airfoil |
GB1530256A (en) * | 1975-04-01 | 1978-10-25 | Rolls Royce | Cooled blade for a gas turbine engine |
US4017209A (en) * | 1975-12-15 | 1977-04-12 | United Technologies Corporation | Turbine rotor construction |
US4086757A (en) * | 1976-10-06 | 1978-05-02 | Caterpillar Tractor Co. | Gas turbine cooling system |
US4712979A (en) * | 1985-11-13 | 1987-12-15 | The United States Of America As Represented By The Secretary Of The Air Force | Self-retained platform cooling plate for turbine vane |
US4752184A (en) * | 1986-05-12 | 1988-06-21 | The United States Of America As Represented By The Secretary Of The Air Force | Self-locking outer air seal with full backside cooling |
US5350277A (en) * | 1992-11-20 | 1994-09-27 | General Electric Company | Closed-circuit steam-cooled bucket with integrally cooled shroud for gas turbines and methods of steam-cooling the buckets and shrouds |
JP3188105B2 (ja) | 1994-07-11 | 2001-07-16 | 三菱重工業株式会社 | ガスタービンの動翼 |
US5634766A (en) * | 1994-08-23 | 1997-06-03 | General Electric Co. | Turbine stator vane segments having combined air and steam cooling circuits |
DE19643716A1 (de) * | 1996-10-23 | 1998-04-30 | Asea Brown Boveri | Schaufelträger für einen Verdichter |
JP3316415B2 (ja) * | 1997-05-01 | 2002-08-19 | 三菱重工業株式会社 | ガスタービン冷却静翼 |
JP2955252B2 (ja) * | 1997-06-26 | 1999-10-04 | 三菱重工業株式会社 | ガスタービン動翼チップシュラウド |
GB9815611D0 (en) * | 1998-07-18 | 1998-09-16 | Rolls Royce Plc | Improvements in or relating to turbine cooling |
US6179555B1 (en) * | 1998-10-06 | 2001-01-30 | Pratt & Whitney Canada Corp. | Sealing of T.O.B.I feed plenum |
GB2365930B (en) * | 2000-08-12 | 2004-12-08 | Rolls Royce Plc | A turbine blade support assembly and a turbine assembly |
US6454526B1 (en) * | 2000-09-28 | 2002-09-24 | Siemens Westinghouse Power Corporation | Cooled turbine vane with endcaps |
-
2001
- 2001-06-27 DE DE10131073A patent/DE10131073A1/de not_active Withdrawn
- 2001-06-28 DE DE10131370A patent/DE10131370A1/de not_active Withdrawn
- 2001-11-30 EP EP01128573A patent/EP1215363B1/de not_active Expired - Lifetime
- 2001-11-30 EP EP01128572A patent/EP1215364B1/de not_active Expired - Lifetime
- 2001-11-30 DE DE50106966T patent/DE50106966D1/de not_active Expired - Lifetime
- 2001-11-30 US US09/996,684 patent/US6682304B2/en not_active Expired - Fee Related
- 2001-11-30 DE DE50107607T patent/DE50107607D1/de not_active Expired - Lifetime
- 2001-11-30 US US09/996,693 patent/US6589011B2/en not_active Expired - Lifetime
- 2001-12-17 JP JP2001383503A patent/JP2002201907A/ja active Pending
Also Published As
Publication number | Publication date |
---|---|
EP1215363A3 (de) | 2004-01-02 |
JP2002201907A (ja) | 2002-07-19 |
EP1215363A2 (de) | 2002-06-19 |
US20020136635A1 (en) | 2002-09-26 |
DE50107607D1 (de) | 2006-02-16 |
EP1215364A2 (de) | 2002-06-19 |
DE10131073A1 (de) | 2002-06-20 |
EP1215364A3 (de) | 2004-01-02 |
US6682304B2 (en) | 2004-01-27 |
DE50106966D1 (de) | 2005-09-08 |
EP1215364B1 (de) | 2005-08-03 |
US6589011B2 (en) | 2003-07-08 |
DE10131370A1 (de) | 2002-06-20 |
US20020127103A1 (en) | 2002-09-12 |
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