EP1219787B1 - Gasturbinenschaufel und Gasturbine - Google Patents
Gasturbinenschaufel und Gasturbine Download PDFInfo
- Publication number
- EP1219787B1 EP1219787B1 EP00128576A EP00128576A EP1219787B1 EP 1219787 B1 EP1219787 B1 EP 1219787B1 EP 00128576 A EP00128576 A EP 00128576A EP 00128576 A EP00128576 A EP 00128576A EP 1219787 B1 EP1219787 B1 EP 1219787B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- vane
- blade
- turbine blade
- platform
- 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
- F01D5/12—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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F01D25/14—Casings modified therefor
- F01D25/145—Thermally insulated casings
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/502—Thermal properties
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/601—Fabrics
Definitions
- the invention relates to a gas turbine blade with a Airfoil and one adjacent to the airfoil Platform area for delimiting a hot gas channel Gas turbine, in which the Gastubinenschaufel can be installed.
- the invention also relates to a gas turbine with such Gas turbine blade.
- a gas turbine blade is apparent from DE 26 28 807 A.
- the gas turbine blade is directed along a blade axis and has an airfoil along the blade axis and a platform area. Extends in the platform area transverse to the blade axis a platform from the blade away radially outward.
- Such a platform forms one Part of a flow channel for a working fluid, which flows through a gas turbine, in which the turbine blade installed is.
- a gas turbine occur in this flow channel very high temperatures. This will cause the hot gas exposed surface of the platform heavily thermally stressed. This requires cooling of the platform.
- For cooling the platform is in front of the side facing away from the hot gas the platform arranged a perforated wall element.
- the object of the invention is the specification of a gas turbine blade, which has a particularly low demand for cooling air.
- Another object of the invention is the specification of a Gas turbine with a particularly low demand for cooling air.
- the object directed to a gas turbine blade is achieved according to the invention solved by specifying a gas turbine blade with an airfoil and one adjacent to the airfoil Platform area for delimiting a hot gas channel a gas turbine, in which the gas turbine blade can be installed is, wherein the platform area has a metal platform, on a ceramic cover by means of a mechanical Fastener rests fastened.
- the hot gas duct limiting platform of a gas turbine blade with a mechanically attached, ceramic cover to provide.
- the metal platform becomes effective in front of the hot gas channel shielded by flowing hot gas. Accordingly, the Metal platform significantly less cooled. In certain circumstances may even be based entirely on cooling the metal platform be waived. This has a significantly reduced need Cooling air result, which in turn the efficiency of a Gas turbine increases, in which the gas turbine blade installed is.
- the gas turbine blade of the proposed type is also also very easy to produce, as a conventional gas turbine blade only in terms of their radial dimensioning something has to be changed so that the ceramic cover flush with the hot gas duct.
- the gas turbine blade otherwise it can be made as usual especially by casting.
- the ceramic cover can be later by means of the mechanical fastener on the Metal platform can be placed and fastened.
- the object directed to a gas turbine solved by specifying a gas turbine with a gas turbine shovel according to one of the embodiments described above.
- the gas turbine blade is in the axial direction a flow channel of the gas turbine between two blades arranged, wherein the second ceramic cover extends in the axial direction just so far that they do not is striped by one of the blades. This will securely prevents the ceramic cover from passing through each here adjacent, rotating past her blades is damaged by rubbing.
- FIG. 1 shows schematically a gas turbine 1.
- the gas turbine 1 has a compressor 3 connected in series, one Combustion chamber 5 and a turbine part 7.
- the turbine part 7 has a hot gas channel 9.
- Guide vanes 11 arranged and with a housing 8 of the turbine part 7 connected.
- Blades 13 arranged with a gas turbine rotor 15 are connected.
- air is in the Compressor 3 compressed and the combustion chamber 5 fed. There it is burnt with the addition of fuel.
- the resulting hot exhaust gas 17 then flows through the hot gas channel 9 and offset the gas turbine rotor 15 at a Action on the blades 13 in rotation.
- FIG. 2 shows a section of a hot gas channel 9 a Gas turbine 1.
- Hot gas entering from the combustion chamber 17 is introduced into the hot gas channel 9 via a first guide vane 11a initiated.
- the first vane 11a is not part of one further illustrated first vane ring.
- the first Guide vane 11a follows in the flow direction of the hot gas 17th a first blade 13a.
- the first blade 13a follows in the flow direction of the hot gas 17, a second vane 11b.
- the second vane 11b follows in the flow direction of the hot gas 17, a second blade 13b.
- In the hot gas duct 9 still further blade stages can follow.
- the first vane 11a is over a mounting area 21 a connected to the housing 8 of the gas turbine 1.
- a platform area 22 closes with a metal platform 23a.
- the metal platform 23a has a surface 25a facing the hot gas channel 9.
- a ceramic cover 27a on the surface 25a. The attachment of the ceramic cover 27a becomes later explained with reference to FIG.
- the second vane 11b is analogous to theirs Attachment 21b connected to the housing 8 and has also on its metal platform 23b, a ceramic cover 27b on.
- the second vane 11b is adjacent to the ceramic cover 27b a hot gas channel 9 passing through Airfoil 24b on.
- the airfoil 24b becomes on the radially inner side by a second ceramic Cover 47 limited, which on the hot gas channel.
- 9 facing side 48 of a second metal platform 41 rests, which is associated with a second platform area 42.
- the second metal platform 41 is adjacent to a réelleringverhakung 43, which carries an inner ring 45.
- the thermally very resistant ceramic Covers 27 a, 27 b, 47 practically do not have to be cooled by cooling air. Also for the metal platforms 23a, 23b, 41 largely eliminates the need for cooling. As a result, the cooling air requirement for the gas turbine. 1 considerably lowered. This in turn has an increase in efficiency for the gas turbine 1 result.
- a mechanical Attachment of the ceramic covers 27a, 27b, 47 to the metal platforms 23a, 23b, 41 also results in a manufacturing technology very cheap and simple design, the also in a simple manner by replacing the ceramic Covers 27a, 27b, 47 in a later service quickly and can be maintained inexpensively.
- the ceramic cover 47 has an axial length L, the just dimensioned is that the adjacent blades Do not stain 13a, 13b. This excludes that the rotating blades 13a, 13b, the ceramic cover 47 damage.
- the ceramic covers 27a, 27b, 47 consist in their main body of mullite and also have a sealing outer sealing layer 50 on, which prevents a detachment of solid particles. Such Solid particles could otherwise erode Effect on the arranged in the hot gas duct 9 gas turbine blades 11, 13 have.
- Each ceramic cover 27a, 27b, 47 also has an integral mat 52, which in the ceramic Basic body is poured.
- Figure 3 shows a gas turbine vane 11.
- the gas turbine vane 11 corresponds to the gas turbine guide vane 11b from Figure 2.
- Closer shown is the structure of the ceramic Cover 27. This consists of two halves 27d, 27s. there the one half 27d adjoins a pressure side 63 of the airfoil 24 on. The second half 27s is adjacent to a suction side 61 of the airfoil 24 at.
- the ceramic cover 27 has on its narrow sides one of these narrow sides circumferential Longitudinal groove 65 on.
- the second ceramic cover 47 is in FIG divided two halves 47d, 47s and also has a circumferential groove 65 on.
- the attachment area 21 corresponds the mounting portion 21b of Figure 2.
- the metal platform 23 with its hot gas channel side surface 25 corresponds the metal platform 23b with its hot gas channel side surface 25b from FIG. 2.
- FIG. 4 shows how a ceramic cover 27 is connected to the gas turbine guide vane 11. At least with its the airfoil 24 facing narrow side 67 the ceramic cover 27 via the groove 65 in engagement with a mechanical fastener 71, which serves as a resilient Sheet metal is connected to the metal platform 23.
- a mechanical fastener 71 which serves as a resilient Sheet metal is connected to the metal platform 23.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- Figur 1 eine Gasturbine,
- Figur 2 einen Teil eines Heißgaskanales einer Gasturbine,
- Figur 3 eine Gasturbinenleitschaufel und
- Figur 4 die Befestigung einer keramischen Abdeckung.
Claims (11)
- Gasturbinenschaufel (11,13) mit einem Schaufelblatt (24) und einem an das Schaufelblatt (24) angrenzenden Plattformbereich (22), wobei der Plattformbereich (22) eine Metallplattform (23) aufweist, auf der eine, keramische Abdeckung (27) mittels eines mechanischen Befestigungsmittels (71) austauschbar befestigt aufliegt.
- Gasturbinenschaufel (11,13) nach Anspruch 1, bei der die keramische Abdeckung (27) aus zwei Hälften (27d,27s) besteht.
- Gasturbinenschaufel (11,13) nach Anspruch 2, bei der eine der Hälften (27s) an eine Saugseite (61) des Schaufelblattes (24) und die andere Hälfte (27d) an eine Druckseite (63) des Schaufelblattes (24) angrenzt.
- Gasturbinenschaufel (11,13) nach Anspruch 1, bei der das mechanische Befestigungsmittel (71) eine mit der Gasturbinenschaufel (11,13) fest verbundene Feder ist.
- Gasturbinenschaufel (11,13) nach Anspruch 4, bei der die Feder in eine Nut (65) der keramischen Abdeckung (27) eingreift, welche Nut (65) entlang einer an das Schaufelblatt (24) angrenzenden Schmalseite verläuft.
- Gasturbinenschaufel (11,13) nach Anspruch 1, bei der ein Fixiersockel (73) auf der Metallplattform (23) angeordnet ist, der in die keramische Abdeckung (27) eingreift.
- Gasturbinenschaufel (11,13) nach Anspruch 1, ausgebildet als Leitschaufel mit einem zweiten Plattformbereich (42), der das Schaufelblatt (24) einschliessend dem Plattformbereich (22) gegenüberliegt, wobei der zweite Plattformbereich (42) eine zweite Metallplattform (41) aufweist, auf der eine zweite keramische Abdeckung (47) mittels eines zweiten mechanischen Befestigungsmittels (71) befestigt aufliegt.
- Gasturbinenschaufel (11,13) nach Anspruch 1, bei der die keramische Abdeckung (27) eine integrale Matte (52) aufweist, durch die bei einem Bruch der keramischen Abdeckung (27) die Bruchstücke in einem Verbund gehalten werden.
- Gasturbinenschaufel (11,13) nach Anspruch 1, bei der die keramische Abdeckung (27) Mullit aufweist.
- Gasturbinenschaufel (11,13) nach Anspruch 9, bei der die keramische Abdeckung (27) eine äussere Versiegelungsschicht (50) gegen eine Partikelablösung aufweist.
- Verwendung einer Gasturbinenschaufel (11,13) nach einem der vorhergehenden Ansprüche in einer Gasturbine.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00128576A EP1219787B1 (de) | 2000-12-27 | 2000-12-27 | Gasturbinenschaufel und Gasturbine |
DE50011923T DE50011923D1 (de) | 2000-12-27 | 2000-12-27 | Gasturbinenschaufel und Gasturbine |
CA002366184A CA2366184A1 (en) | 2000-12-27 | 2001-12-24 | Gas turbine blade/vane and gas turbine |
JP2001391104A JP4125891B2 (ja) | 2000-12-27 | 2001-12-25 | ガスタービン翼とガスタービン |
US10/032,926 US6652228B2 (en) | 2000-12-27 | 2001-12-27 | Gas turbine blade and gas turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00128576A EP1219787B1 (de) | 2000-12-27 | 2000-12-27 | Gasturbinenschaufel und Gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1219787A1 EP1219787A1 (de) | 2002-07-03 |
EP1219787B1 true EP1219787B1 (de) | 2005-12-21 |
Family
ID=8170840
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00128576A Expired - Lifetime EP1219787B1 (de) | 2000-12-27 | 2000-12-27 | Gasturbinenschaufel und Gasturbine |
Country Status (5)
Country | Link |
---|---|
US (1) | US6652228B2 (de) |
EP (1) | EP1219787B1 (de) |
JP (1) | JP4125891B2 (de) |
CA (1) | CA2366184A1 (de) |
DE (1) | DE50011923D1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2010149528A1 (de) | 2009-06-23 | 2010-12-29 | Siemens Aktiengesellschaft | Ringförmiger strömungskanalabschnitt für eine turbomaschine |
Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6786052B2 (en) * | 2002-12-06 | 2004-09-07 | 1419509 Ontario Inc. | Insulation system for a turbine and method |
EP1528343A1 (de) * | 2003-10-27 | 2005-05-04 | Siemens Aktiengesellschaft | Keramischer Hitzeschildstein mit eingebetteten Verstärkungselementen zur Auskleidung einer Gasturbinenbrennkammerwand |
JP4346412B2 (ja) * | 2003-10-31 | 2009-10-21 | 株式会社東芝 | タービン翼列装置 |
US7789621B2 (en) * | 2005-06-27 | 2010-09-07 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine airfoil |
EP1843009A1 (de) * | 2006-04-06 | 2007-10-10 | Siemens Aktiengesellschaft | Leitschaufelsegment einer thermischen Strömungsmaschine, zugehöriges Herstellungsverfahren sowie thermische Strömungsmaschine |
FR2906296A1 (fr) * | 2006-09-26 | 2008-03-28 | Snecma Sa | Dispositif de fixation d'une aube fixe dans un carter annulaire de turbomachine, turboreacteur incorporant le dispositif et procede de montage de l'aube. |
US20080298973A1 (en) * | 2007-05-29 | 2008-12-04 | Siemens Power Generation, Inc. | Turbine vane with divided turbine vane platform |
US8408874B2 (en) | 2008-04-11 | 2013-04-02 | United Technologies Corporation | Platformless turbine blade |
US8973375B2 (en) * | 2008-12-31 | 2015-03-10 | Rolls-Royce North American Technologies, Inc. | Shielding for a gas turbine engine component |
US8840359B2 (en) * | 2010-10-13 | 2014-09-23 | The United States Of America, As Represented By The Secretary Of The Navy | Thermally insulating turbine coupling |
RU2547542C2 (ru) * | 2010-11-29 | 2015-04-10 | Альстом Текнолоджи Лтд | Осевая газовая турбина |
EP2644828A1 (de) * | 2012-03-29 | 2013-10-02 | Siemens Aktiengesellschaft | Modulare Turbinenschaufel mit Plattform |
EP2644834A1 (de) * | 2012-03-29 | 2013-10-02 | Siemens Aktiengesellschaft | Turbinenschaufel sowie zugehöriges Verfahren zum Herstellen einer Turbinenschaufel |
US9376916B2 (en) | 2012-06-05 | 2016-06-28 | United Technologies Corporation | Assembled blade platform |
FR2993927B1 (fr) * | 2012-07-27 | 2014-08-22 | Snecma | Piece de modification du profil d'une veine aerodynamique |
WO2014163701A2 (en) | 2013-03-11 | 2014-10-09 | Uskert Richard C | Compliant intermediate component of a gas turbine engine |
JP2017537255A (ja) * | 2014-10-28 | 2017-12-14 | シーメンス エナジー インコーポレイテッド | モジュール式のタービンベーン |
US10309257B2 (en) | 2015-03-02 | 2019-06-04 | Rolls-Royce North American Technologies Inc. | Turbine assembly with load pads |
US10161266B2 (en) * | 2015-09-23 | 2018-12-25 | General Electric Company | Nozzle and nozzle assembly for gas turbine engine |
US10767498B2 (en) | 2018-04-03 | 2020-09-08 | Rolls-Royce High Temperature Composites Inc. | Turbine disk with pinned platforms |
US10890081B2 (en) | 2018-04-23 | 2021-01-12 | Rolls-Royce Corporation | Turbine disk with platforms coupled to disk |
US10577961B2 (en) | 2018-04-23 | 2020-03-03 | Rolls-Royce High Temperature Composites Inc. | Turbine disk with blade supported platforms |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
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US3867065A (en) * | 1973-07-16 | 1975-02-18 | Westinghouse Electric Corp | Ceramic insulator for a gas turbine blade structure |
IT1079131B (it) | 1975-06-30 | 1985-05-08 | Gen Electric | Perfezionato raffreddamento applicabile particolarmente a elementi di turbomotori a gas |
DE2628708A1 (de) | 1976-06-25 | 1977-12-29 | Siemens Ag | Nach dem impuls-echoverfahren arbeitendes ultraschall-bildgeraet |
US4643636A (en) * | 1985-07-22 | 1987-02-17 | Avco Corporation | Ceramic nozzle assembly for gas turbine engine |
JPH076366B2 (ja) * | 1985-08-20 | 1995-01-30 | 三菱重工業株式会社 | ガスタ−ビン静翼 |
JP2807465B2 (ja) * | 1988-05-07 | 1998-10-08 | 株式会社神戸製鋼所 | セラミクス耐熱複合部品 |
JP2777609B2 (ja) * | 1989-09-27 | 1998-07-23 | 株式会社日立製作所 | セラミック静翼 |
DE4017861A1 (de) * | 1990-06-02 | 1991-12-05 | Mtu Muenchen Gmbh | Leitkranz fuer eine gasturbine |
US5492445A (en) * | 1994-02-18 | 1996-02-20 | Solar Turbines Incorporated | Hook nozzle arrangement for supporting airfoil vanes |
DE19605858A1 (de) * | 1996-02-16 | 1997-08-21 | Claussen Nils | Verfahren zur Herstellung von Al¶2¶O¶3¶-Aluminid-Composites, deren Ausführung und Verwendung |
US6235370B1 (en) * | 1999-03-03 | 2001-05-22 | Siemens Westinghouse Power Corporation | High temperature erosion resistant, abradable thermal barrier composite coating |
DE50007554D1 (de) * | 1999-03-24 | 2004-09-30 | Siemens Ag | Leitschaufel und leitschaufelkranz für eine strömungsmaschine, sowie bauteil zur begrenzung eines strömungskanals |
-
2000
- 2000-12-27 EP EP00128576A patent/EP1219787B1/de not_active Expired - Lifetime
- 2000-12-27 DE DE50011923T patent/DE50011923D1/de not_active Expired - Lifetime
-
2001
- 2001-12-24 CA CA002366184A patent/CA2366184A1/en not_active Abandoned
- 2001-12-25 JP JP2001391104A patent/JP4125891B2/ja not_active Expired - Fee Related
- 2001-12-27 US US10/032,926 patent/US6652228B2/en not_active Expired - Fee Related
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2010149528A1 (de) | 2009-06-23 | 2010-12-29 | Siemens Aktiengesellschaft | Ringförmiger strömungskanalabschnitt für eine turbomaschine |
EP2282014A1 (de) | 2009-06-23 | 2011-02-09 | Siemens Aktiengesellschaft | Rinförmiger Strömungskanalabschnitt für eine Turbomaschine |
Also Published As
Publication number | Publication date |
---|---|
US6652228B2 (en) | 2003-11-25 |
EP1219787A1 (de) | 2002-07-03 |
CA2366184A1 (en) | 2002-06-27 |
JP2002201912A (ja) | 2002-07-19 |
DE50011923D1 (de) | 2006-01-26 |
JP4125891B2 (ja) | 2008-07-30 |
US20020182067A1 (en) | 2002-12-05 |
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