EP1219787B1 - Aube de turbine à gaz et turbine à gaz - Google Patents

Aube de turbine à gaz et turbine à gaz Download PDF

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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
Application number
EP00128576A
Other languages
German (de)
English (en)
Other versions
EP1219787A1 (fr
Inventor
Peter Tiemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to DE50011923T priority Critical patent/DE50011923D1/de
Priority to EP00128576A priority patent/EP1219787B1/fr
Priority to CA002366184A priority patent/CA2366184A1/fr
Priority to JP2001391104A priority patent/JP4125891B2/ja
Priority to US10/032,926 priority patent/US6652228B2/en
Publication of EP1219787A1 publication Critical patent/EP1219787A1/fr
Application granted granted Critical
Publication of EP1219787B1 publication Critical patent/EP1219787B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/22—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)

Claims (11)

  1. Aube (11, 13) de turbine à gaz ayant une lame (24) et une partie (22) de plateforme voisine de la lame (24), la partie (22) de plateforme comportant une plateforme (23) métallique sur laquelle s'applique, en y étant fixé de manière à pouvoir être remplacé à l'aide d'un moyen (71) de fixation mécanique, un recouvrement (27) en céramique.
  2. Aube (11, 13) de turbine à gaz suivant la revendication 1, dans laquelle le recouvrement (27) en céramique est constitué de deux moitiés (27d, 27s).
  3. Aube (11, 13) de turbine à gaz suivant la revendication 2, dans laquelle l'une des moitiés (27s) est voisine d'un extrados (61) de la lame (24) et l'autre moitié (27d) d'un intrados (63) de la lame (24).
  4. Aube (11, 13) de turbine à gaz suivant la revendication 1, dans laquelle le moyen (71) de fixation mécanique est un ressort relié rigidement à l'aube (11, 13) de la turbine à gaz.
  5. Aube (11, 13) de turbine à gaz suivant la revendication 4, dans laquelle le ressort pénètre dans une rainure (65) du recouvrement en céramique, rainure (65) qui s'étend le long d'un petit côté voisin de la lame (24).
  6. Aube (11, 13) de turbine à gaz suivant la revendication 1, dans laquelle une moulure (73) de fixation est ménagée sur la plateforme (23) métallique et pénètre dans le recouvrement (27) en céramique.
  7. Aube (11, 13) de turbine à gaz suivant la revendication 1, constituée en aube directrice ayant une deuxième partie (42) de plateforme qui est opposée à la lame (24), y compris à la partie (22) de plateforme, la deuxième partie (42) de plateforme ayant une deuxième plateforme (41) métallique sur laquelle repose en étant fixé à l'aide d'un deuxième moyen (71) de fixation mécanique un deuxième recouvrement (47) en céramique.
  8. Aube (11, 13) de turbine à gaz suivant la revendication 1, dans laquelle le recouvrement (27) en céramique comporte une nappe (52) d'un seul tenant par laquelle, si le recouvrement (27) en céramique se rompt, les fragments sont maintenus en un ensemble.
  9. Aube (11, 13) de turbine à gaz suivant la revendication 1, dans laquelle le recouvrement (27) en céramique comprend de la mullite.
  10. Aube (11, 13) de turbine à gaz suivant la revendication 9, dans laquelle le recouvrement (27) en céramique a une couche (50) extérieure de scellement empêchant des particules de se détacher.
  11. Utilisation d'une aube (11, 13) de turbine à gaz suivant l'une des revendications précédentes dans une turbine à gaz.
EP00128576A 2000-12-27 2000-12-27 Aube de turbine à gaz et turbine à gaz Expired - Lifetime EP1219787B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
DE50011923T DE50011923D1 (de) 2000-12-27 2000-12-27 Gasturbinenschaufel und Gasturbine
EP00128576A EP1219787B1 (fr) 2000-12-27 2000-12-27 Aube de turbine à gaz et turbine à gaz
CA002366184A CA2366184A1 (fr) 2000-12-27 2001-12-24 Aube et ailette de turbine a gaz ainsi que turbine a gaz
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 (fr) 2000-12-27 2000-12-27 Aube de turbine à gaz et turbine à gaz

Publications (2)

Publication Number Publication Date
EP1219787A1 EP1219787A1 (fr) 2002-07-03
EP1219787B1 true EP1219787B1 (fr) 2005-12-21

Family

ID=8170840

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00128576A Expired - Lifetime EP1219787B1 (fr) 2000-12-27 2000-12-27 Aube de turbine à gaz et turbine à gaz

Country Status (5)

Country Link
US (1) US6652228B2 (fr)
EP (1) EP1219787B1 (fr)
JP (1) JP4125891B2 (fr)
CA (1) CA2366184A1 (fr)
DE (1) DE50011923D1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010149528A1 (fr) 2009-06-23 2010-12-29 Siemens Aktiengesellschaft Segment de canal d'écoulement de forme annulaire pour une turbomachine

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EP1528343A1 (fr) * 2003-10-27 2005-05-04 Siemens Aktiengesellschaft Tuile réfractaire avec des éléments de renforcement noyés pour révêtement d'une chambre de combustion de turbines à gaz
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 (fr) * 2006-04-06 2007-10-10 Siemens Aktiengesellschaft Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine
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
EP2627909B1 (fr) * 2010-10-13 2019-07-10 The Government of the United States of America as represented by the Secretary of the Navy Ensemble rotor avec couplage de turbine thermo-isolant
RU2547542C2 (ru) * 2010-11-29 2015-04-10 Альстом Текнолоджи Лтд Осевая газовая турбина
EP2644828A1 (fr) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Aube de turbine modulaire avec plateforme
EP2644834A1 (fr) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Aube de turbine ainsi que son procédé de fabrication correspondant
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
CA2897965C (fr) 2013-03-11 2020-02-25 David J. Thomas Composant intermediaire conforme d'une turbine a gaz
CN107075952A (zh) * 2014-10-28 2017-08-18 西门子能源公司 模块化涡轮叶片
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

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Cited By (2)

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Publication number Priority date Publication date Assignee Title
WO2010149528A1 (fr) 2009-06-23 2010-12-29 Siemens Aktiengesellschaft Segment de canal d'écoulement de forme annulaire pour une turbomachine
EP2282014A1 (fr) 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Section de canal d'écoulement annulaire pour une turbomachine

Also Published As

Publication number Publication date
DE50011923D1 (de) 2006-01-26
JP2002201912A (ja) 2002-07-19
JP4125891B2 (ja) 2008-07-30
US20020182067A1 (en) 2002-12-05
CA2366184A1 (fr) 2002-06-27
US6652228B2 (en) 2003-11-25
EP1219787A1 (fr) 2002-07-03

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